Stabilizers

Draft · under review

This draft is for study only; it is not a maintenance document. Sources: FAA AD 2019-14-14 (84 FR 41609, 15 Aug 2019), downloaded from govinfo.gov on 2026-11-10 and read as literal Federal Register text (page numbers are Federal Register pages 41609-41611); FAA AD 2019-18-04 (84 FR 50301, 25 Sep 2019), local file read as literal Federal Register text, only the subject code (para (d) p.50303) and the term "rudder servo actuators" (para (e) p.50303) used; FAA JASC code table (grouping and code descriptions only; printed page = PDF page minus 7, both given for the definition pages PDF pp.50-52; the code table page PDF p.11 is cited by PDF page only); NTSB/AAR-04/04 (Level 3, context only), section 1.6.1, printed pp.15-18. Model names are given as each source prints them; nothing said about one model is extended to the family. The "55-xx" headings are this site's grouping, following FAA JASC chapter 55 "Stabilizers". AD 2019-14-14 prints only "Code 55, Stabilizers" as subject and AD 2019-18-04 prints "Code 27, Flight controls; 55, Stabilizers."; AD 2019-14-14 names "SRM 55-30-00" and "AMM Task 55-36-11" only as references inside its text, and this draft gives nothing from those manuals. The TCDS EASA.A.172 and the Airbus A300-600 Airport Planning AC were not used for this chapter (see Bekliyor). No licensed manual was used. The ADs are described only as to what they address; this draft gives no compliance times and no procedures. Where an AD reports EASA text, the bullet says so.

A300 and A300-600 models named per source · FAA Airworthiness Directives

55-00 Stabilizers: general

The FAA JASC table lists chapter "55 STABILIZERS" with: 5500 EMPENNAGE STRUCTURE; 5510 HORIZONTAL STABILIZER STRUCTURE; 5511 HORIZONTAL STABILIZER, SPAR/RIB; 5512 HORIZONTAL STABILIZER, PLATE/SKIN; 5513 HORIZONTAL STABILIZER, TAB STRUCTURE; 5514 HORIZ STAB MISCELLANEOUS STRUCTURE; 5520 ELEVATOR STRUCTURE; 5521 ELEVATOR, SPAR/RIB STRUCTURE; 5522 ELEVATOR, PLATES/SKIN STRUCTURE; 5523 ELEVATOR, TAB STRUCTURE; 5524 ELEVATOR MISCELLANEOUS STRUCTURE; 5530 VERTICAL STABILIZER STRUCTURE; 5531 VERTICAL STABILIZER, SPAR/RIB STRUCT.; 5532 VERTICAL STABILIZER, PLATES/SKIN; 5533 VENTRAL STRUCTURE; 5534 VERT. STAB. MISCELLANEOUS STRUCTURE; 5540 RUDDER STRUCTURE; 5541 RUDDER, SPAR/RIB; 5542 RUDDER, PLATE/SKIN; 5543 RUDDER, TAB STRUCTURE; 5544 RUDDER MISCELLANEOUS STRUCTURE; 5550 EMPENNAGE FLT. CONT., ATTACH FITTING; 5551 HORIZONTAL STABILIZER, ATTACH FITTING; 5552 ELEVATOR/TAB, ATTACH FITTINGS; 5553 VERT. STAB., ATTACH FITTINGS; 5554 RUDDER/TAB, ATTACH FITTINGS; 5597 STABILIZER SYSTEM WIRING. Titles are as the table on PDF p.11 prints them; the definition headings on PDF pp.50-52 differ in places. This is an FAA code table, not a description of the A300.^[1][1]
JASC describes code 5500 as: "The horizontal and vertical stabilizers include the structure of the elevator and rudder.".^[1]
Both ADs below give their subject as an Air Transport Association (ATA) of America code that includes 55, Stabilizers: AD 2019-14-14 prints "Air Transport Association (ATA) of America Code 55, Stabilizers." and AD 2019-18-04 prints "Air Transport Association (ATA) of America Code 27, Flight controls; 55, Stabilizers.".^[2][3]

55-30 Vertical stabilizer

JASC definitions: JASC describes code 5530 as "The structural aspects of the fixed vertical surface attached to the fuselage including the dorsal fin." and code 5553 as "For specific reports pertaining to the fittings on the vertical stabilizer which are used to support equipment within the structure.".^[1][1]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: Applicability, as printed in the AD: "Airbus SAS Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes", certificated in any category, "as identified in European Aviation Safety Agency (EASA) AD 2019-0006, dated January 17, 2019". The AD also lists Model A310 airplanes, which are not part of this chapter.^[2]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: The AD's summary calls the A300 B4-600, B4-600R and F4-600R series airplanes and the Model A300 C4-605R Variant F airplanes, "collectively called Model A300-600 series airplanes".^[2]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: The AD's own statement of why it was issued: it "was prompted by a determination that a certain aircraft maintenance manual task provided instructions for a visual inspection of composite and metallic vertical tailplane (VTP) attachment fittings, but the inspection method did not specify detection of delamination length, which could possibly extend beyond the defined allowable limits.".^[2]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: The AD's own statement of the unsafe condition: VTP attachment fittings "that could be delaminated beyond allowable limits, which, if not detected and corrected, could lead to failure of the VTP attachment fittings, possibly resulting in loss of control of the airplane.".^[2][2]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: What the AD addresses (the AD's own summary): a review of airplane maintenance records and, depending on the results, one-time detailed and ultrasonic inspections of the affected parts and applicable corrective actions, "as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference".^[2]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: Reported from EASA: the AD quotes the EASA AD 2019-0006 text ("The MCAI states") naming "AMM Task 55-36-11" as the aircraft maintenance manual task concerned, and saying that "the inspection method included in the AMM does not allow detection of delamination length". The same quoted text reports that Airbus issued "the applicable SB [service bulletin] to provide non-destructive test instructions, which allow detection of delaminated area(s) before exceeding the limits". The content of the AMM task and of the service bulletin is not given here.^[2]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: Reported from EASA: the AD quotes the EASA AD as requiring "a review of maintenance records and, depending on the result, a one-time detailed inspection (DET) of the affected parts, followed by an ultrasonic (US) inspection, and, depending on findings, accomplishment of applicable corrective action(s).".^[2]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: The AD itself (not EASA) adds that, where paragraph (3) of the EASA AD refers to "discrepancies", the AD "defines discrepancies as any damage or delamination found outside of specified allowable damage limits.". In its discussion of a comment, the AD describes those limits as "specified in the inspection tasks in the service information (including reference to SRM 55-30-00)"; the SRM is mentioned only as named and its content is not given.^[2][2]
Vertical tailplane (VTP) attachment fittings: AD 2019-14-14: The AD also replaces wording of the EASA AD in places (paragraph (h)(2) and (h)(3) concern the wording on incomplete maintenance records and on the word "concurrently"); this draft does not describe those replacements or their timing.^[2]

55-40 Rudder

JASC describes code 5540 as "For reports pertaining to the structural aspects of the vertical airfoil hinged to the vertical stabilizer. Does not include the actuators, actuator mechanism or mounting which are filed in JASC code 2720.".^[1]
Cross-reference: the rudder servo actuators (AD 2019-18-04, whose subject line includes "55, Stabilizers" along with "27, Flight controls") are covered in the ATA 27 chapter of this site and are not repeated here.^[3]

Context (NTSB report)

Level 3 context only. This section describes what NTSB/AAR-04/04 addresses; it publishes no technical values from it. The report concerns the in-flight separation of the vertical stabilizer of American Airlines Flight 587, "Airbus Industrie A300-605R, N14053", on November 12, 2001; it was adopted October 26, 2004.^[4][4]
Section 1.6.1 "Vertical Stabilizer and Rudder" states that the "A300-600 vertical stabilizer and rudder were constructed with composite materials", consisting primarily of carbon or glass fibers held in an epoxy polymer, identified in the report as carbon fiber reinforced plastics (CFRP) or glass fiber reinforced plastics (GFRP).^[4]
The section describes the vertical stabilizer as consisting of a torque box, a leading edge and tip, and a trailing edge, and names the torque box as the main structural component. It lists the torque box's constituent parts (spars, skin panels, ribs, stringers) and describes how the leading edge and tip are attached to it and how the trailing edge panels are attached through a trailing edge support structure. Counts and materials of those parts are not repeated here.^[4]
The section describes how the vertical stabilizer is attached to the aft fuselage, using main attachment fittings and transverse load fittings shown in the report's figure 4, and shows a main attachment lug in figure 5. It states that the fittings are made from CFRP. Numbers, thicknesses and positions of the fittings are not repeated here.^[4]
The section describes the rudder as attached to the aft portion of the vertical stabilizer, built from CFRP and GFRP over a honeycomb core, with hinge arm assemblies, a support strut assembly and servo controls described in the report. Counts and materials of the hinge parts are not repeated here.^[4]
The Level 1 AD above speaks of "composite and metallic vertical tailplane (VTP) attachment fittings" for the airplanes it lists (Model A300-600 series and Model A310 series together), while this report states "All of the fittings are made from a CFRP material."; neither document relates the two statements, and they are given as printed. No Level 1 source read for this draft prints the numbers of the fittings, ribs or stringers.^[2][2][4]

Not yet covered

Structural description of the A300-600 vertical stabilizer and rudder (torque box construction, number of ribs and stringers, number and type of attachment fittings, hinge arrangement): among the documents read for this draft, printed in the NTSB report (Level 3) and in no Level 1 source. Not published. Horizontal stabilizer and elevator (55-10, 55-20): no A300 content from a Level 1 source was read. The text layer of all 68 pages of the TCDS EASA.A.172 (Issue 08) was searched for stabilizer, stabiliser, tailplane, elevator, empennage, rudder, fin, THS, HTP, VTP and trim, and prints nothing on the structure or surfaces of the horizontal stabilizer or elevator. The word "tailplane" occurs twice, both times for a fuel tank: for the A310-300 series (p.38), and in the special condition "For A 300 B4-600 R, A300 F4-600 R and A300 C4-600 R series, a special condition relative to the installation of a fuel tank in the horizontal tailplane used to control the center of gravity (letter DGAC 53927 SFACT/TC)." (p.60). The word "Trim" occurs only as a fuel tank name. These fuel tank statements are not used in this chapter. Tail dimensions (stabilizer span, fin height) in the Airbus A300-600 Airport Planning AC chapter 2.2: the pages are drawings and were not rendered or read for this draft. Content of EASA AD 2019-0006 (the document AD 2019-14-14 incorporates): the EASA AD site was not queried; only the FAA AD's quotation of it is used. Which A300 models carry which of the "composite and metallic" VTP attachment fittings the AD speaks of: the AD lists applicable models but does not say which airplanes within them have which fittings. Component names for the elevator and trim system, and structural component names for the rudder: no Level 1 source read for this draft prints them. AD 2019-18-04 prints "rudder servo actuators" (see 55-40; treated under ATA 27), and the TCDS prints "Trim" only as a fuel tank name.

Sources

Every fact on this page links to a public source. Accessed dates are shown per document.

FAA Joint Aircraft System/Component (JASC) Code Table and Definitions, Information last updated October 27, 2008 (2008-10-27) — PDF p.11, PDF pp.50-52; printed pp.43-45; PDF p.50, printed p.43; PDF p.51, p.52; printed pp.44-45; PDF p.51, printed p.44. https://www.faa.gov/sites/faa.gov/files/JASC_Code.pdf · accessed 2026-11-10
FAA AD 2019-14-14 — Airbus SAS airplanes (A300-600 included), Issue 84 FR 41609 (2019-08-15) — para (d) p.41610; para (c) p.41610; Summary p.41609; para (e) p.41611; Discussion p.41609; the clause from "which, if not detected" also in para (e) p.41611; para (h)(5) p.41611; Comments p.41610; para (h)(2)-(3) p.41611. https://www.govinfo.gov/content/pkg/FR-2019-08-15/html/2019-17507.htm · accessed 2026-11-10
FAA AD 2019-18-04 — Airbus SAS airplanes (A300-600 included), Issue 84 FR 50301 (2019-09-25) — para (d) p.50303; para (d), para (e) p.50303. https://www.govinfo.gov/content/pkg/FR-2019-09-25/html/2019-20755.htm · accessed 2026-11-10
NTSB/AAR-04/04 — In-Flight Separation of Vertical Stabilizer, American Airlines Flight 587, A300-605R N14053, AAR-04/04 (2004-10-26) — cover page; PDF p.3; §1.6.1 p.15; §1.6.1 p.15-17; §1.6.1 p.17-18. https://www.ntsb.gov/investigations/AccidentReports/Reports/AAR0404.pdf · accessed 2026-11-10

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