Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes, 11346-11347 [E8-3930]

Download as PDF 11346 § 797.22 Federal Register / Vol. 73, No. 42 / Monday, March 3, 2008 / Rules and Regulations Voluntary repayment agreement. (a) In response to the Notice, an employee may propose to repay the debt voluntarily in lieu of salary offset by submitting a written proposed repayment schedule to NCUA. Any proposal under this section must be received by NCUA within 15 calendar days after receipt of the Notice. (b) In response to a timely proposal by the employee, NCUA shall notify the employee whether the employee’s proposed repayment schedule is acceptable. NCUA has the discretion to accept, reject, or propose to the employee a modification of the proposed repayment schedule. (1) If NCUA decides that the proposed repayment schedule is unacceptable, the employee shall have 15 calendar days from the date of the decision in which to file a request for a hearing. (2) If NCUA decides that the proposed repayment schedule is acceptable or the employee agrees to a modification proposed by NCUA, an agreement shall be put in writing and signed by both the employee and NCUA. § 797.23 Certification where NCUA is the creditor agency. (a) NCUA shall issue a certification in all cases where the hearing official determines that a debt exists or the employee admits the existence and amount of the debt, as for example, by failing to request a hearing. (b) The certification must be in writing and state: (1) That the employee owes the debt; (2) The amount and basis of the debt; (3) The date the federal government’s right to collect the debt first accrued; (4) The date the employee was notified of the debt, the action(s) taken pursuant to NCUA’s regulations, and the dates such actions were taken; (5) If the collection is to be made by lump-sum payment, the amount and date such payment will be collected; (6) If the collection is to be made in installments, the amount or percentage of disposable pay to be collected in each installment and, if NCUA wishes, the desired commencing date of the first installment, if a date other than the next officially established pay period; and (7) A statement that NCUA’s regulation on salary offset has been approved by OPM pursuant to 5 CFR part 550, subpart K. rmajette on PROD1PC64 with RULES § 797.24 Certification where NCUA is the paying agency. (a) Upon issuance of a proper certification by NCUA or upon receipt of a proper certification from another creditor agency, NCUA shall send the employee a written notice of salary offset. VerDate Aug<31>2005 14:18 Feb 29, 2008 Jkt 214001 (b) Such written notice of salary offset shall advise the employee of the: (1) Certification that has been issued by NCUA or received from another creditor agency; (2) Amount of the debt and of the deductions to be made; and (3) Date and pay period when the salary offset will begin. (c) If NCUA is not the creditor agency, NCUA shall provide a copy of the notice to the creditor agency and advise the creditor agency of the dollar amount to be offset and the pay period when the offset will begin. § 797.25 Recovery from final check or other payments due a separated employee. (a) Lump-sum deduction from final check. In order liquidate a debt, a lumpsum deduction exceeding 15 percent of disposable pay may be made pursuant to 31 U.S.C. 3716 from any final salary payment due a former employee, whether the former employee was separated voluntarily or involuntarily. (b) Lump-sum deductions from other sources. Whenever an employee subject to salary offset is separated from NCUA, and the balance of the debt cannot be liquidated by offset of the final salary payment, NCUA may offset any later payments of any kind to the former employee to collect the balance of the debt pursuant to 31 U.S.C. 3716. [FR Doc. E8–3799 Filed 2–29–08; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–29249; Directorate Identifier 2007–NM–112–AD; Amendment 39–15294; AD 2007–25–12] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; correction. AGENCY: SUMMARY: The FAA is correcting a typographical error in an existing airworthiness directive (AD) that was published in the Federal Register on December 10, 2007 (72 FR 69593). The error resulted in a potential for confusion regarding the applicability of the AD. This AD applies to certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires PO 00000 Frm 00042 Fmt 4700 Sfmt 4700 inspections of the landing gear (LG) selector valve 40GA and the LG door selector valve 41GA, to identify a possible hydraulic leak. The corrective action includes replacing the LG selector valve 40GA and/or the LG door selector valve 41GA if necessary. DATES: Effective January 14, 2008. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: On November 21, 2007, the FAA issued AD 2007–25–12, amendment 39–15294 (72 FR 69593, December 10, 2007), for certain Airbus Model A318, A319, A320, and A321 series airplanes. The AD requires inspections of the landing gear (LG) selector valve 40GA and the LG door selector valve 41GA, to identify a possible hydraulic leak. The corrective action includes replacing the LG selector valve 40GA and/or the LG door selector valve 41GA if necessary. As published, the AD applies to airplanes identified in paragraphs (c)(1) ‘‘and’’ (c)(2) of this AD instead of those identified in paragraph (c)(1) ‘‘or’’ (c)(2) of this AD. This change is relieving in nature, and no other part of the regulatory information has been changed; therefore, the final rule is not republished in the Federal Register. The effective date of this AD remains January 14, 2008. § 39.13 [Corrected] I In the Federal Register of December 10, 2007, on page 69594, in the second column, paragraph (c) of AD 2007–25– 12 is corrected to read as follows: * * * * * (c) This AD applies to Airbus Model A318, A319, A320, and A321 series airplanes, certificated in any category, E:\FR\FM\03MRR1.SGM 03MRR1 Federal Register / Vol. 73, No. 42 / Monday, March 3, 2008 / Rules and Regulations except those identified in paragraph (c)(1) or (c)(2) of this AD. * * * * * Issued in Renton, Washington, on February 25, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–3930 Filed 2–29–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0226; Directorate Identifier 2008–NM–016–AD; Amendment 39–15404; AD 2008–05–10] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757–200, –200PF, and –200CB Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. rmajette on PROD1PC64 with RULES AGENCY: Examining the AD Docket SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 757–200, –200PF, and –200CB series airplanes powered by Rolls-Royce engines. The existing AD currently requires repetitive inspections of the shim installation between the vertical flange and bulkhead, and repair if necessary. The existing AD also requires, for certain airplanes, an inspection for cracking of the four critical fastener holes in the horizontal flange, and repair if necessary. This new AD retains the requirements of the existing AD, and requires that the existing action be performed on airplanes without conclusive records of previous inspections. This AD results from our determination that an operator did not maintain records of previous inspections that are necessary to determine the appropriate corrective actions. We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-to-diagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane. DATES: This AD becomes effective March 18, 2008. On August 24, 2007 (72 FR 44753, August 9, 2007), the Director of the Federal Register approved the VerDate Aug<31>2005 14:18 Feb 29, 2008 Jkt 214001 incorporation by reference of Boeing Alert Service Bulletin 757–54A0047, Revision 3, dated June 27, 2007. We must receive any comments on this AD by May 2, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6449; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion On July 31, 2007, we issued AD 2007– 16–13, amendment 39–15152 (72 FR 44753, August 9, 2007). That AD applies to certain Boeing Model 757–200, –200PF, and –200CB series airplanes powered by Rolls-Royce engines. That AD requires repetitive inspections of the shim installation between the vertical flange and bulkhead, and repair if necessary. That AD also requires, for certain airplanes, an inspection for cracking of the four critical fastener holes in the horizontal flange, and repair if necessary. That AD resulted from reports of cracking in the pylon under bolts that appear to be PO 00000 Frm 00043 Fmt 4700 Sfmt 4700 11347 undamaged during the existing AD inspections. The actions specified in that AD are intended to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-todiagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane. Actions Since AD Was Issued Since we issued that AD, we have determined that some operators have not maintained records of findings (positive or negative) beyond one year of inspections conducted in accordance with AD 2007–16–13 or AD 2005–12–04 (which AD 2007–16–13 superseded). Therefore, there is no way to determine conclusively what the findings were during previous inspections. Inspection findings during previous inspections are necessary to determine what additional corrective actions need to be taken in order to adequately address the unsafe condition identified in this AD. This AD has new requirements for these airplanes that do not have records of findings during previous inspections. FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other airplanes of the same type design. For this reason, we are issuing this AD to supersede AD 2007–16–13. This new AD retains the requirements of the existing AD. This AD also requires that the existing requirements be performed on airplanes for which there are no conclusive records of previous inspections. FAA’s Justification and Determination of the Effective Date We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-todiagonal brace fitting. These conditions could result in damage to the strut and consequent separation of the strut and engine from the airplane. Because of our requirement to promote safe flight of civil aircraft and thus, the critical need to ensure the structural integrity of the aft torque bulkhead and the strut-todiagonal brace fitting for the engine strut and the short compliance time involved with this action, this AD must be issued immediately. Because an unsafe condition exists that requires the immediate adoption of this AD, we find that notice and opportunity for prior public comment hereon are impracticable and that good E:\FR\FM\03MRR1.SGM 03MRR1

Agencies

[Federal Register Volume 73, Number 42 (Monday, March 3, 2008)]
[Rules and Regulations]
[Pages 11346-11347]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-3930]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29249; Directorate Identifier 2007-NM-112-AD; 
Amendment 39-15294; AD 2007-25-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
Series Airplanes

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

ACTION: Final rule; correction.

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

SUMMARY: The FAA is correcting a typographical error in an existing 
airworthiness directive (AD) that was published in the Federal Register 
on December 10, 2007 (72 FR 69593). The error resulted in a potential 
for confusion regarding the applicability of the AD. This AD applies to 
certain Airbus Model A318, A319, A320, and A321 series airplanes. This 
AD requires inspections of the landing gear (LG) selector valve 40GA 
and the LG door selector valve 41GA, to identify a possible hydraulic 
leak. The corrective action includes replacing the LG selector valve 
40GA and/or the LG door selector valve 41GA if necessary.

DATES: Effective January 14, 2008.

ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: On November 21, 2007, the FAA issued AD 
2007-25-12, amendment 39-15294 (72 FR 69593, December 10, 2007), for 
certain Airbus Model A318, A319, A320, and A321 series airplanes. The 
AD requires inspections of the landing gear (LG) selector valve 40GA 
and the LG door selector valve 41GA, to identify a possible hydraulic 
leak. The corrective action includes replacing the LG selector valve 
40GA and/or the LG door selector valve 41GA if necessary.
    As published, the AD applies to airplanes identified in paragraphs 
(c)(1) ``and'' (c)(2) of this AD instead of those identified in 
paragraph (c)(1) ``or'' (c)(2) of this AD.
    This change is relieving in nature, and no other part of the 
regulatory information has been changed; therefore, the final rule is 
not republished in the Federal Register.
    The effective date of this AD remains January 14, 2008.


Sec.  39.13   [Corrected]

0
In the Federal Register of December 10, 2007, on page 69594, in the 
second column, paragraph (c) of AD 2007-25-12 is corrected to read as 
follows:
* * * * *
    (c) This AD applies to Airbus Model A318, A319, A320, and A321 
series airplanes, certificated in any category,

[[Page 11347]]

except those identified in paragraph (c)(1) or (c)(2) of this AD.
* * * * *

    Issued in Renton, Washington, on February 25, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-3930 Filed 2-29-08; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.