[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
