AD 2000-05-25

This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires installation of a placard prescribing special procedures to be followed when operating at certain flight levels with the engine and airframe anti-ice switch ON; modification of the air brake auto-retract function; and a revision to the Airplane Flight Manual (AFM) relative to altitude and operating limitations associated with flight in icing conditions above 26,000 feet. This amendment requires installation/replacement of new placards. This amendment also provides for a terminating modification for the AFM revision and installation/replacement of placards. This amendment is prompted by reports of uncommanded engine thrust reductions (rollback) when operating in certain icing conditions that exist in the vicinity of thunderstorms. The actions specified by this AD are intended to prevent enginepower rollback during flight in icing conditions, a condition that could result in insufficient power to sustain flight.

Final rule

2000-05-25 BRITISH AEROSPACE REGIONAL AIRCRAFT (Formerly British Aerospace Regional Aircraft Limited, Avro International Aerospace Division; British Aerospace, PLC; British Aerospace Commercial Aircraft Limited): Amendment 39-11635. Docket 98-NM-174-AD. Supersedes AD 96-14-09, Amendment 39-9694.

Applicability: Model BAe 146-100A, -200A, and -300A series airplanes, certificated in any category; equipped with AlliedSignal ALF502R- series engines.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (g)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent engine power rollback during flight in icing conditions, a condition that could result in insufficient power to sustain flight, accomplish the following:

RESTATEMENT OF REQUIREMENTS OF AD 96-14-09, AMENDMENT 39-9694
Placard Installation
(a) For airplanes listed in British Aerospace Service Bulletin SB.11-97-01285A, Revision 1, dated April 3, 1992: Within 30 days after December 17, 1992 (the effective date of AD 92-24-09, amendment 39-8415), install a placard below the ice protection switches on the flight deck overhead panel to include additional procedures to be followed when operating at certain flight levels with the engine and airframe anti-ice switch ON, in accordance with British Aerospace Service Bulletin SB.11-97-01285A, Revision 1, dated April 3, 1992.

Modification
(b) For airplanes listed in British Aerospace Service Bulletin SB.11-97-01285A, Revision 1, dated April 3, 1992: Within 30 days after December 17, 1992 (the effective date of AD 92-24-09, amendment 39-8415), modify the air brake auto-retract function, in accordance with British Aerospace Service Bulletin SB.11-97-01285A, Revision 1, dated April 3, 1992.

Airplane Flight Manual Revision
(c) Within 6 days after July 22, 1996 (the effective date of AD 96-14-09, amendment 39-9694), amend the FAA- approved Airplane Flight Manual (AFM) as required by paragraphs (c)(1) and (c)(2) of this AD.

(1) Remove the following Temporary Revisions (TR) from the Limitations Section and Normal/Abnormal Procedures Section, as applicable:

(i) For Model BAe 146-100A series airplanes: TR 30, Issue No. 2 (Document No. BAe 3.3), dated February 1994.

(ii) For Model BAe 146-200A series airplanes:TR 41, Issue No. 2 (Document No. BAe 3.3), dated February 1994, or TR 42, Issue No. 2 (Document No. BAe 3.3), dated February 1994, as applicable.

(iii) For Model BAe 146-300A series airplanes: TR 23, Issue No. 2 (Document No. BAe 3.3), dated February 1994.

(2) Insert the following TR's into the Limitations Section and the Normal/Abnormal Procedures/Handling Section, as applicable.

(i) For Model BAe 146-100A series airplanes: TR 32, Issue No. 2 (Document BAe 3.3), dated July 1996.

(ii) For Model BAe 146-200A series airplanes: TR 44, Issue No. 2 (Document BAe 3.6), dated July 1996.

(iii) For Model BAe 146-300A series airplanes: TR 25, Issue No. 2 (Document BAe 3.11), dated July 1996.

(d) When the TR's specified in paragraph (c)(2) have been incorporated into an AFM General Revision, the applicable AFM General Revision may be inserted into the corresponding FAA-approved AFM, provided the information contained in the AFM General Revision corresponds identically to that specified in TR 32, TR 44, or TR 25.

NEW REQUIREMENTS OF THIS AD
Placard Installation
(e) Within 30 days after the effective date of this AD, install a placard on the flight deck to indicate that a 26,000 feet altitude limitation in icing is applicable, and replace the ice protection panel placard with a new placard for N2 limitations, in accordance with British Aerospace Service Bulletin SB.11-137-30405A, dated March 26, 1998. Upon accomplishment of this placard installation, the placard required by paragraph (a) of this AD may be removed.

Terminating Modification (Including Modification Required by AD 99-15-06)
(f) Modification of all four engines [i.e., reduction of the length core-flow/fan-flow splitter (cut-back splitter); modification of the splitter lip insulating baffle; installation of a heated exit guide vane (EGV); relocation of the engine anti-ice air source to the combustor bleed plenum; installation of a new anti-ice valve with improved couplings; and installation of improved insulated connections], and insertions of AFM revisions, in accordance with British Aerospace Service Bulletin SB.71-72-30473A, dated July 8, 1998, or Revision 1, dated November 2, 1998; constitutes terminating action for the requirements of this AD. After the modification is accomplished, the AFM revisions and placards required by paragraphs (c), (d), and (e) of this AD may be removed.

NOTE 2: British Aerospace Service Bulletin SB.71-72-30473A, dated July 8, 1998, and Revision 1, dated November 2, 1998, only describe procedures for installation of engines that have been modified in accordance with the requirements of AD 99-15-06, amendment 39-11225.

Alternative Methods of Compliance
(g) (1) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

(2) Alternative methods of compliance, approved previously in accordance with AD 96-14-09, amendment 39-9694, are approved as alternative methods of compliance with this AD.

Special Flight Permits
(h) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

Incorporation by Reference
(i) The actions shall be done in accordance with British Aerospace Service Bulletin SB.11-97-01285A, Revision 1, dated April 3, 1992; Airplane Flight Manual Temporary Revision 32, Issue No. 2 (Document BAe 3.3), dated July 1996; Airplane Flight Manual Temporary Revision 44, Issue No. 2 (Document BAe 3.6), dated July 1996; Airplane Flight Manual Temporary Revision 25, Issue No. 2 (Document BAe 3.11), dated July 1996; and British Aerospace Service Bulletin SB.11-137-30405A, dated March 26, 1998; as applicable.

(1) The incorporation by reference of British Aerospace Service Bulletin SB.11-137-30405A, dated March 26, 1998, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The incorporation by reference of British Aerospace Service Bulletin SB.11-97-01285A, Revision 1, dated April 3, 1992, was approved previously by the Director of the Federal Register as of December 17, 1992 (57 FR 53548, November 12, 1992).

(3) The incorporation by reference of Airplane Flight Manual Temporary Revision 32, Issue No. 2 (Document BAe 3.3), dated July 1996; Airplane Flight Manual Temporary Revision 44, Issue No. 2 (Document BAe 3.6), dated July 1996; and Airplane Flight Manual Temporary Revision 25, Issue No. 2 (Document BAe 3.11), dated July 1996; was approved previously by the Director of the Federal Register as of July 22, 1996 (61 FR 37199, July 17, 1996).

(4) Copies may be obtained from British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

NOTE 4: The subject of this AD is addressed in British airworthiness directives 004-03-98 and 003-06-96, Revision 1.

(j) This amendment becomes effective on April 24, 2000.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 96-14-09, amendment 39-9694 (61 FR 37199, July 17, 1996), which is applicable to all British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, was published in the Federal Register on December 9, 1999 (64 FR 68956). The action proposed to continue to require installation of a placard prescribing special procedures to be followed when operating at certain flight levels with the engine and airframe anti-ice switch ON; modification of the air brake auto-retract function; and a revision to the Airplane Flight Manual (AFM) relative to altitude and operating limitations associated with flight in icing conditions above 26,000 feet. The action also proposed to add a requirement for installation/replacement of new placards. The action also proposed to provide for a terminating modification for the AFM revision and installation/replacement of placards.

Comments Received
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.

Request to Revise Applicability
One commenter requests that the proposed AD be revised to include only airplanes with ALF502R- series engines installed. The commenter states that AlliedSignal has provided substantiation to the FAA's Engine and Propeller Directorate to demonstrate that the ALF507-1H engine is not subject to the engine rollback phenomenon; therefore, airplanes with these engines installed should be excluded from the applicability of the AD.

The FAA concurs. The FAA has determined that British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes equipped with ALF502R- series engines are those that should be subject to the requirements of this AD. The FAA has revised the applicability of the final rule accordingly.

Request to Revise Reference to Terminating Modification
The same commenter requests that the proposed AD be revised to eliminate references to an "optional terminating modification." The proposed AD provides for accomplishment of the actions described in British Aerospace Service Bulletin SB.71-72-30473A, dated July 8, 1998, or Revision 1, dated November 2, 1998, as terminating action for the requirements of this AD. This service bulletin defines various modifications necessary to implement the rollback prevention package, including an engine modification, which is described in AlliedSignal Engines Service Bulletin ALF/LF72-1020. The commenter states that referral to these modifications as optional is misleading, because the engine modification is actually required via separate rulemaking action [FAA AD 99-15-06, amendment 39-11225 (64 FR 38557, July 19, 1999)]. The commenter suggests that the Summary of the proposed AD be revised to state that "the proposed AD would also provide terminating action by incorporation of the engine modification." For the same reasons, the commenter also suggests that the wording in the paragraph titled "Actions Since Issuance of Previous Rule" in the proposed AD be revised.

The FAA concurs that reference to the modifications as optional in this AD may be misleading, since the engine modification is already required by FAA AD 99-15-06. The FAA's intent was to allow for accomplishment of the modifications prior to the compliance threshold required by AD 99-15-06, and to provide for removal of the AFM revision and placards required by this AD following accomplishment of the modifications. The FAA has revised the appropriate sections of this final rule to remove the word "optional" in reference to the terminating modification. The FAA also has removed the associated cost estimates from the Cost Impact information, below. However, since the paragraph titled "Actions Since Issuance of Previous Rule" in the proposed AD is not restated in the final rule, no change is made to that paragraph of the AD.

Conclusion
After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes previously described. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact
There are approximately 40 airplanes of U.S. registry that will be affected by this AD.

The actions that are currently required by AD 96-14-09 take approximately 4 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the previously required actions on U.S. operators is estimated to be $9,600, or $240 per airplane.

The new actions that are required by this new AD will take approximately 1 work hour per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures,the cost impact of the new requirements of this AD on U.S. operators is estimated to be $2,400, or $60 per airplane.

The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.

Regulatory Impact
The regulations adopted herein will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.

39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-9694 (61 FR 37199, July 17, 1996), and by adding a new airworthiness directive (AD), amendment 39-11635, to read as follows: