Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 Airplanes, 32982-32984 [05-11056]

Download as PDF 32982 Federal Register / Vol. 70, No. 108 / Tuesday, June 7, 2005 / Rules and Regulations forth in the Regulatory Flexibility Act or the Small Business Size Standards set out in regulations issued by the Small Business Administration at 13 CFR part 121. Backfit Analysis The NRC has determined that the backfit rule (10 CFR 50.109 or 10 CFR 72.62) does not apply to this direct final rule because this amendment does not involve any provisions that would impose backfits as defined. Therefore, a backfit analysis is not required. Small Business Regulatory Enforcement Fairness Act In accordance with the Small Business Regulatory Enforcement Fairness Act of 1996, the NRC has determined that this action is not a major rule and has verified this determination with the Office of Information and Regulatory Affairs, Office of Management and Budget. List of Subjects in 10 CFR Part 72 Administrative practice and procedure, Criminal penalties, Manpower training programs, Nuclear materials, Occupational safety and health, Penalties, Radiation protection, Reporting and recordkeeping requirements, Security measures, Spent fuel, Whistleblowing. I For the reasons set out in the preamble and under the authority of the Atomic Energy Act of 1954, as amended; the Energy Reorganization Act of 1974, as amended; and 5 U.S.C. 552 and 553; the NRC is adopting the following amendments to 10 CFR Part 72. PART 72—LICENSING REQUIREMENTS FOR THE INDEPENDENT STORAGE OF SPENT NUCLEAR FUEL, HIGH-LEVEL RADIOACTIVE WASTE, AND REACTOR-RELATED GREATER THAN CLASS C WASTE 1. The authority citation for part 72 continues to read as follows: 10153, 10155, 10157, 10161, 10168); sec. 1704, 112 Stat. 2750 (44 U.S.C. 3504 note). Section 72.44(g) also issued under secs. 142(b) and 148(c), (d), Pub. L. 100–203, 101 Stat. 1330–232, 1330–236 (42 U.S.C. 10162(b), 10168(c),(d)). Section 72.46 also issued under sec. 189, 68 Stat. 955 (42 U.S.C. 2239); sec. 134, Pub. L. 97–425, 96 Stat. 2230 (42 U.S.C. 10154). Section 72.96(d) also issued under sec. 145(g), Pub. L. 100–203, 101 Stat. 1330–235 (42 U.S.C. 10165(g)). Subpart J also issued under secs. 2(2), 2(15), 2(19), 117(a), 141(h), Pub. L. 97–425, 96 Stat. 2202, 2203, 2204, 2222, 2244 (42 U.S.C. 10101, 10137(a), 10161(h)). Subparts K and L are also issued under sec. 133, 98 Stat. 2230 (42 U.S.C. 10153) and sec. 218(a), 96 Stat. 2252 (42 U.S.C. 10198). 2. In § 72.214, Certificate of Compliance 1014 is revised to read as follows: I § 72.214 List of approved spent fuel storage casks. * * * * * Certificate Number: 1014. Initial Certificate Effective Date: June 1, 2000. Amendment Number 1 Effective Date: July 15, 2002. Amendment Number 2 Effective Date: June 7, 2005. SAR Submitted by: Holtec International. SAR Title: Final Safety Analysis Report for the HI–STORM 100 Cask System. Docket Number: 72–1014. Certificate Expiration Date: June 1, 2020 Model Number: HI–STORM 100 * * * * * Dated at Rockville, Maryland, this 25th day of May, 2005. For the Nuclear Regulatory Commission. Luis A. Reyes, Executive Director for Operations. [FR Doc. 05–11216 Filed 6–6–05; 8:45 am] BILLING CODE 7590–01–P I DEPARTMENT OF TRANSPORTATION Authority: Secs. 51, 53, 57, 62, 63, 65, 69, 81, 161, 182, 183, 184, 186, 187, 189, 68 Stat. 929, 930, 932, 933, 934, 935, 948, 953, 954, 955, as amended, sec. 234, 83 Stat. 444, as amended (42 U.S.C. 2071, 2073, 2077, 2092, 2093, 2095, 2099, 2111, 2201, 2232, 2233, 2234, 2236, 2237, 2238, 2282); sec. 274, Pub. L. 86–373, 73 Stat. 688, as amended (42 U.S.C. 2021); sec. 201, as amended, 202, 206, 88 Stat. 1242, as amended, 1244, 1246 (42 U.S.C. 5841, 5842, 5846); Pub. L. 95–601, sec. 10, 92 Stat. 2951 as amended by Pub. L. 102– 486, sec. 7902, 106 Stat. 3123 (42 U.S.C. 5851); sec. 102, Pub. L. 91–190, 83 Stat. 853 (42 U.S.C. 4332); secs. 131, 132, 133, 135, 137, 141, Pub. L. 97–425, 96 Stat. 2229, 2230, 2232, 2241, sec. 148, Pub. L. 100–203, 101 Stat. 1330–235 (42 U.S.C. 10151, 10152, VerDate jul<14>2003 16:06 Jun 06, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20724; Directorate Identifier 2004–NM–233–AD; Amendment 39–14115; AD 2005–11–13] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 airplanes. This AD requires repetitive inspections for cracks of the fuselage pressure skin above the left and right main landing gear (MLG) bay. This AD also requires corrective action, including related investigative actions, if leaks are found. This AD is prompted by reports of cracks in the fuselage pressure skin above the left and right MLG bay. We are issuing this AD to detect and correct fatigue cracking in the fuselage pressure skin above the left and right MLG bay; such fatigue cracking could adversely affect the structural integrity of the fuselage and its ability to maintain pressure differential. DATES: This AD becomes effective July 12, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of July 12, 2005. ADDRESSES: For service information identified in this AD, contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2005–20724; the directorate identifier for this docket is 2004–NM– 233–AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain BAE Systems (Operations) Limited Model BAe 146 airplanes. That action, published in the Federal Register on March 30, 2005 (70 FR 16173), proposed to require repetitive inspections for cracks of the fuselage pressure skin above the left and right main landing gear (MLG) bay. The action also proposed AD to require E:\FR\FM\07JNR1.SGM 07JNR1 32983 Federal Register / Vol. 70, No. 108 / Tuesday, June 7, 2005 / Rules and Regulations corrective action, including related investigative actions, if leaks are found. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been submitted on the proposed AD or on the determination of the cost to the public. Explanation of Change to Applicability We have revised the applicability of the proposed AD to identify model designations as published in the most recent type certificate data sheet for the affected model. adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Average labor rate per hour Work hours Inspection, per inspection cycle ... 7 $65 $0 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. (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. We prepared a regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD 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. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; PART 39—AIRWORTHINESS DIRECTIVES VerDate jul<14>2003 16:06 Jun 06, 2005 Jkt 205001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2005–11–13 BAE Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Amendment 39– Frm 00007 Fmt 4700 $455 18 Fleet cost $8,190, per inspection cycle. 14115. Docket No. FAA–2005–20724; Directorate Identifier 2004–NM–233–AD. Effective Date (a) This AD becomes effective July 12, 2005. Affected ADs (b) None. Applicability (c) This AD applies to BAE Systems (Operations) Limited Model BAe 146–100A, –200A, and –300A series airplanes, certificated in any category; except those on which BAe Modification HCM00972A or HCM00972C has been accomplished. Unsafe Condition (d) This AD was prompted by reports of cracks in the fuselage pressure skin above the left and right main landing gear (MLG) bay. We are issuing this AD to detect and correct fatigue cracking in the fuselage pressure skin above the left and right MLG bay; such fatigue cracking could adversely affect the structural integrity of the fuselage and its ability to maintain pressure differential. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Initial and Repetitive Inspections [Amended] I PO 00000 Number of U.S.-registered airplanes Cost per airplane Parts Sfmt 4700 (f) At the times specified in Table 1 of this AD, inspect the fuselage pressure skin above the left and right MLG bay for cracks in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin 53–170, dated August 8, 2003. E:\FR\FM\07JNR1.SGM 07JNR1 32984 Federal Register / Vol. 70, No. 108 / Tuesday, June 7, 2005 / Rules and Regulations TABLE 1.—COMPLIANCE TIMES For airplanes listed in paragraph (c) of this AD— Do initial inspections— And do repetitive inspections thereafter— On which neither BAe modification HCM00744M nor HCM00850A has been accomplished. Prior to the accumulation of 15,000 total flight cycles or within 500 flight cycles after the effective date of this AD, whichever occurs later. Prior to the accumulation of 15,000 total flight cycles or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. At intervals not to exceed 1,000 flight cycles. On which either BAe modification HCM00744M or HCM00850A has been accomplished. On which both BAe modifications HCM00744M and HCM00850A have been accomplished. Corrective Action (g) If any crack is found during any inspection required by paragraph (f) of this AD, do the corrective action and any related investigative actions, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin 53–170, dated August 8, 2003, except as required by paragraph (h) of this AD. (h) If any cracking is found during any inspection or related investigative action required by this AD, and the service bulletin recommends contacting BAE Systems for appropriate action: Before further flight, repair the cracks according to a method approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the Civil Aviation Authority (or its delegated agent). No Reporting (i) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (j) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (k) British airworthiness directive G–2004– 0004, dated February 26, 2004, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use BAE Systems (Operations) Limited Inspection Service Bulletin 53–170, dated August 8, 2003, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– VerDate jul<14>2003 16:06 Jun 06, 2005 Jkt 205001 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on May 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11056 Filed 6–6–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19988; Directorate Identifier 2004–NM–30–AD; Amendment 39– 14111; AD 2005–11–09] RIN 2120–AA64 Airworthiness Directives; Boeing Model 727–200 Series Airplanes Equipped With a No. 3 Cargo Door Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 727–200 series airplanes equipped with a No. 3 cargo door. This AD requires repetitive detailed and high frequency eddy current inspections for cracking of the forward, lower corner frame and forward end of the lower beam of the No. 3 cargo door, and corrective actions if necessary. The AD provides an optional terminating action for the repetitive inspections. This AD is prompted by reports of cracking at the forward, lower corner frame and lower beam of the No. 3 cargo door. We are issuing this AD to detect and correct cracking of the forward, lower corner frame and forward end of the lower beam of the No. 3 cargo door, which could result in failure of the affected door stops, loss of the cargo door, and consequent rapid decompression of the airplane. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 At intervals not to exceed 3,000 flight cycles. This AD becomes effective July 12, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of July 12, 2005. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Washington, DC. This docket number is FAA–2004–19988; the directorate identifier for this docket is 2004–NM– 30–AD. FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6456; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Boeing Model 727– 200 series airplanes equipped with a No. 3 cargo door. That action, published in the Federal Register on January 5, 2005 (70 FR 729), proposed to require repetitive detailed and high frequency eddy current inspections for cracking of the forward, lower corner frame and forward end of the lower beam of the No. 3 cargo door, and corrective actions if necessary. That action also proposed to provide an optional terminating action for the repetitive inspections. DATES: Comments We provided the public the opportunity to participate in the development of this AD. We have E:\FR\FM\07JNR1.SGM 07JNR1

Agencies

[Federal Register Volume 70, Number 108 (Tuesday, June 7, 2005)]
[Rules and Regulations]
[Pages 32982-32984]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11056]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20724; Directorate Identifier 2004-NM-233-AD; 
Amendment 39-14115; AD 2005-11-13]
RIN 2120-AA64


Airworthiness Directives; BAE Systems (Operations) Limited Model 
BAe 146 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain BAE Systems (Operations) Limited Model BAe 146 airplanes. This 
AD requires repetitive inspections for cracks of the fuselage pressure 
skin above the left and right main landing gear (MLG) bay. This AD also 
requires corrective action, including related investigative actions, if 
leaks are found. This AD is prompted by reports of cracks in the 
fuselage pressure skin above the left and right MLG bay. We are issuing 
this AD to detect and correct fatigue cracking in the fuselage pressure 
skin above the left and right MLG bay; such fatigue cracking could 
adversely affect the structural integrity of the fuselage and its 
ability to maintain pressure differential.

DATES: This AD becomes effective July 12, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of July 
12, 2005.

ADDRESSES: For service information identified in this AD, contact 
British Aerospace Regional Aircraft American Support, 13850 Mclearen 
Road, Herndon, Virginia 20171.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2005-20724; the directorate 
identifier for this docket is 2004-NM-233-AD.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain BAE Systems (Operations) Limited Model BAe 146 
airplanes. That action, published in the Federal Register on March 30, 
2005 (70 FR 16173), proposed to require repetitive inspections for 
cracks of the fuselage pressure skin above the left and right main 
landing gear (MLG) bay. The action also proposed AD to require

[[Page 32983]]

corrective action, including related investigative actions, if leaks 
are found.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the proposed 
AD or on the determination of the cost to the public.

Explanation of Change to Applicability

    We have revised the applicability of the proposed AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected model.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                      Number of U.S.-
               Action                   Work hours     Average labor       Parts         Cost per       registered                Fleet cost
                                                       rate per hour                     airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection, per inspection cycle....               7             $65              $0            $455              18  $8,190, per inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-11-13 BAE Systems (Operations) Limited (Formerly British 
Aerospace Regional Aircraft): Amendment 39-14115. Docket No. FAA-
2005-20724; Directorate Identifier 2004-NM-233-AD.

Effective Date

    (a) This AD becomes effective July 12, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to BAE Systems (Operations) Limited Model 
BAe 146-100A, -200A, and -300A series airplanes, certificated in any 
category; except those on which BAe Modification HCM00972A or 
HCM00972C has been accomplished.

Unsafe Condition

    (d) This AD was prompted by reports of cracks in the fuselage 
pressure skin above the left and right main landing gear (MLG) bay. 
We are issuing this AD to detect and correct fatigue cracking in the 
fuselage pressure skin above the left and right MLG bay; such 
fatigue cracking could adversely affect the structural integrity of 
the fuselage and its ability to maintain pressure differential.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Initial and Repetitive Inspections

    (f) At the times specified in Table 1 of this AD, inspect the 
fuselage pressure skin above the left and right MLG bay for cracks 
in accordance with the Accomplishment Instructions of BAE Systems 
(Operations) Limited Inspection Service Bulletin 53-170, dated 
August 8, 2003.

[[Page 32984]]



                       Table 1.--Compliance Times
------------------------------------------------------------------------
                                                      And do repetitive
   For airplanes listed in         Do initial            inspections
 paragraph (c) of this AD--       inspections--         thereafter--
------------------------------------------------------------------------
On which neither BAe          Prior to the          At intervals not to
 modification HCM00744M nor    accumulation of       exceed 1,000 flight
 HCM00850A has been            15,000 total flight   cycles.
 accomplished.                 cycles or within
                               500 flight cycles
                               after the effective
                               date of this AD,
                               whichever occurs
                               later.
On which either BAe           Prior to the          At intervals not to
 modification HCM00744M or     accumulation of       exceed 3,000 flight
 HCM00850A has been            15,000 total flight   cycles.
 accomplished.                 cycles or within
On which both BAe              1,000 flight cycles
 modifications HCM00744M and   after the effective
 HCM00850A have been           date of this AD,
 accomplished.                 whichever occurs
                               later.
------------------------------------------------------------------------

Corrective Action

    (g) If any crack is found during any inspection required by 
paragraph (f) of this AD, do the corrective action and any related 
investigative actions, in accordance with the Accomplishment 
Instructions of BAE Systems (Operations) Limited Inspection Service 
Bulletin 53-170, dated August 8, 2003, except as required by 
paragraph (h) of this AD.
    (h) If any cracking is found during any inspection or related 
investigative action required by this AD, and the service bulletin 
recommends contacting BAE Systems for appropriate action: Before 
further flight, repair the cracks according to a method approved by 
the Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate; or the Civil Aviation Authority (or its delegated 
agent).

No Reporting

    (i) Although the service bulletin referenced in this AD 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (j) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.

Related Information

    (k) British airworthiness directive G-2004-0004, dated February 
26, 2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use BAE Systems (Operations) Limited Inspection 
Service Bulletin 53-170, dated August 8, 2003, to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approves the 
incorporation by reference of this document in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. To get copies of the service 
information, contact British Aerospace Regional Aircraft American 
Support, 13850 Mclearen Road, Herndon, Virginia 20171. To view the 
AD docket, go to the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., room PL-401, Nassif 
Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to http://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.

    Issued in Renton, Washington, on May 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-11056 Filed 6-6-05; 8:45 am]
BILLING CODE 4910-13-P