[Federal Register Volume 60, Number 182 (Wednesday, September 20, 1995)]
[Rules and Regulations]
[Pages 48631-48632]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-22855]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-131-AD; Amendment 39-9375; AD 95-19-13]


Airworthiness Directives; British Aerospace Model BAe 146-100A, -
200A, and -300A Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all British Aerospace Model BAe 146-100A, -200A, and -
300A airplanes, that requires repetitive inspections for cracking of 
fuselage frame 29, and repair, if necessary. This amendment is prompted 
by testing that revealed fatigue cracking in the web and inboard flange 
of frame 29. The actions specified by this AD are intended to prevent 
reduced structural integrity of the fuselage due to fatigue cracking in 
frame 29.

DATES: Effective October 20, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 20, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from Avro International Aerospace, Inc., 22111 Pacific Blvd., 
Sterling, Virginia 20166. This information may be examined at the 
Federal Aviation Administration (FAA), Transport Airplane Directorate, 
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all British Aerospace Model BAe 
146-100A, -200A, and -300A airplanes was published in the Federal 
Register on April 20, 1995 (60 FR 19693). That action proposed to 
require repetitive visual inspections to detect cracking of the 
fuselage at frame 29, and repair, if necessary.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.
    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.
    The FAA estimates that 43 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 9 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $23,220, or $540 
per airplane, per inspection cycle.
    The total cost impact figure discussed above is 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.
    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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.

[[Page 48632]]


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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-19-13 British Aerospace Regional Aircraft Limited, AVRO 
International Aerospace Division (Formerly British Aerospace, plc; 
British Aerospace Commercial Aircraft, Limited): Amendment 39-9375. 
Docket 94-NM-131-AD.

    Applicability: All Model BAe 146-100A, -200A, and -3300A 
airplanes, certificated in any category.

    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 use the authority 
provided in paragraph (d) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of the fuselage of the 
airplane due to fatigue cracking in frame 29, accomplish the 
following:
    (a) Perform a detailed visual inspection for cracking of frame 
29 between stringers 12 and 18 on the left and right side of the 
fuselage, in accordance with Avro International Aerospace Inspection 
Service Bulletin S.B. 53-130, dated May 10, 1994. If the polymer 
coating on frame 29 prevents a detailed visual inspection, perform a 
surface eddy current inspection for cracking in accordance with the 
service bulletin. Perform the inspections at the time specified in 
paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable.
    (1) For Model BAe 146-100A airplanes: Perform the inspection 
within 6 months after the effective date of this AD, or prior to the 
accumulation of 30,000 total landings, whichever occurs later. 
Repeat the inspection thereafter at intervals not to exceed 6,000 
landings.
    (2) For Model BAe 146-200A airplanes, and for Model BAe 146-300A 
airplanes other than those airplanes identified in paragraph (a)(3) 
of this AD: Perform the inspection within 6 months after the 
effective date of this AD, or prior to the accumulation of 24,000 
total landings, whichever occurs later. Repeat the inspection 
thereafter at intervals not to exceed 6,000 landings.
    (3) For Model BAe 146-300A airplanes having serial numbers 
E3207, E3212, E3214, E3216, E3218, E3219, and E3222: Perform the 
inspection within 6 months after the effective date of this AD, or 
prior to the accumulation of 13,000 total landings, whichever occurs 
later. Repeat the inspection thereafter at intervals not to exceed 
4,000 landings.
    (b) If any cracking is found during any inspection required by 
paragraph (a) of this AD, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate.
    (c) Accomplishment of the modification of each affected bolt 
position in accordance with Avro International Aerospace Inspection 
Service Bulletin S.B. 53-130, dated May 10, 1994, prior to the 
embodiment times shown in Table 'A' of that service bulletin, 
constitutes terminating action for the repetitive inspections 
required by paragraph (a) of this AD.

    Note 2: Repair Instruction Leaflet (RIL) HC536H9159 provides 
detailed instructions for modification of all bolt positions in the 
affected areas of frame 29.

    (d) 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, Standardization Branch, ANM-113. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Standardization Branch, ANM-113.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (e) 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.
    (f) The inspections and modification shall be done in accordance 
with Avro International Aerospace Inspection Service Bulletin S.B. 
53-130, dated May 10, 1994. This incorporation by reference was 
approved by the Director of the Federal Register in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Avro 
International Aerospace, Inc., 22111 Pacific Blvd., Sterling, 
Virginia 20166. 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.
    (g) This amendment becomes effective on October 20, 1995.

    Issued in Renton, Washington, on September 7, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-22855 Filed 9-19-95; 8:45 am]
BILLING CODE 4910-13-U