Airworthiness Directives; McDonnell Douglas Model DC-8-62, DC-8-63, DC-8-62F, and DC-8-63F Airplanes, 6921-6922 [E7-2416]

Download as PDF Federal Register / Vol. 72, No. 30 / Wednesday, February 14, 2007 / Rules and Regulations 6921 (2) As an option, the service bulletin allows repairs specified in an approved BAE Systems repair scheme. This AD instead requires any repair using this option to be done in accordance with a method approved by either the Manager, International Branch, ANM–116, FAA; or the European Aviation Safety Agency (or its delegated agent). DEPARTMENT OF TRANSPORTATION Examining the Docket Federal Aviation Administration Alternative Methods of Compliance (AMOCs) RIN 2120–AA64 (h)(1) The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Airworthiness Directives; McDonnell Douglas Model DC–8–62, DC–8–63, DC–8–62F, and DC–8–63F Airplanes You may examine the airworthiness directive (AD) docket on the Internet at https://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 street address stated in the ADDRESSES section. Related Information (i) The subject of this AD is also addressed in European Aviation Safety Agency emergency airworthiness directive 2006– 0091–E, dated April 20, 2006. Material Incorporated by Reference (j) You must use BAE Systems (Operations) Limited Alert Inspection Service Bulletin ISB.57–a071, dated April 12, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Renton, Washington, on February 5, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–2414 Filed 2–13–07; 8:45 am] rmajette on PROD1PC67 with RULES BILLING CODE 4910–13–P VerDate Aug<31>2005 15:01 Feb 13, 2007 Jkt 211001 14 CFR Part 39 [Docket No. FAA–2006–26084; Directorate Identifier 2006–NM–063–AD; Amendment 39–14937; AD 2007–04–06] Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC–8–62, DC–8–63, DC–8–62F, and DC–8–63F airplanes. This AD requires revising the wiring for the engine thrust brake circuit and indicating circuit and other specified actions, or rerouting the wiring at plug P1–1762A on the electrical power center generator control panel, as necessary. This AD results from the determination that the thrust reverser systems on these airplanes do not adequately preclude inadvertent deployment of the thrust reversers. We are issuing this AD to prevent inadvertent deployment of the thrust reversers during takeoff or landing, which could result in loss of control of the airplane. DATES: This AD becomes effective March 21, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 21, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: William Bond, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5253; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain McDonnell Douglas Model DC–8–62, DC–8–63, DC–8–62F, and DC–8–63F airplanes. That NPRM was published in the Federal Register on October 19, 2006 (71 FR 61690). That NPRM proposed to require revising the wiring for the engine thrust brake circuit and indicating circuit and other specified actions, or rerouting the wiring at plug P1–1762A on the electrical power center generator control panel, as necessary. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 70 airplanes of the affected design in the worldwide fleet. This AD affects about 45 airplanes of U.S. registry. The required actions take between 1 and 5 work hours per airplane, depending on airplane configuration, at an average labor rate of $80 per work hour. For a certain airplane configuration, required parts cost about $9 per airplane. For a certain other airplane configuration, required parts cost about $2,825 per airplane. Based on these figures, the estimated cost of this AD for U.S. operators is between $4,005 and $145,125, or between $89 and $3,225 per airplane. 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 E:\FR\FM\14FER1.SGM 14FER1 6922 Federal Register / Vol. 72, No. 30 / Wednesday, February 14, 2007 / Rules and Regulations 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. 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 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 Regulatory Findings [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 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 and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. 2007–04–06 McDonnell Douglas: Amendment 39–14937. Docket No. FAA–2006–26084; Directorate Identifier 2006–NM–063–AD. Effective Date (a) This AD becomes effective March 21, 2007. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Model DC–8–62 and DC–8–63 airplanes and Model DC–8–62F and DC–8–63F airplanes, certificated in any category; as identified in McDonnell Douglas DC–8 Service Bulletin 78–95, Revision 2, dated March 10, 1971. Unsafe Condition (d) This AD results from the determination that the thrust reverser systems on McDonnell Douglas Model DC–8–62, DC–8– 63, DC–8–62F, and DC–8–63F airplanes do not adequately preclude inadvertent deployment of the thrust reversers. We are issuing this AD to prevent inadvertent deployment of the thrust reversers during takeoff or landing, which could result in loss of control of the airplane. 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. Modification of Engine Thrust Brake Circuitry (f) Within 27 months after the effective date of this AD, do the applicable action specified in paragraph (f)(1) or (f)(2) of this AD, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of McDonnell Douglas DC–8 Service Bulletin 78–95, Revision 2, dated March 10, 1971; or Revision 1, dated December 29, 1970. (1) Revise the wiring for the engine thrust brake circuit and indicating circuit, and do all other specified actions before further flight after revising the wiring. (2) Reroute the wiring at plug P1–1762A on the electrical power center generator control panel. Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Los Angeles Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (h) You must use McDonnell Douglas DC– 8 Service Bulletin 78–95, Revision 2, dated March 10, 1971; or McDonnell Douglas DC– 8 Service Bulletin 78–95, Revision 1, dated December 29, 1970; to perform the actions that are required by this AD, unless the AD specifies otherwise. McDonnell Douglas DC– 8 Service Bulletin 78–95, Revision 2, dated March 10, 1971, contains the following effective pages: Revision level shown on page 1, 2, 16, 17 .......................................................................................................................................................... 3–15, 18–23 ........................................................................................................................................................ rmajette on PROD1PC67 with RULES Page number 2 1 The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, VerDate Aug<31>2005 15:01 Feb 13, 2007 Jkt 211001 Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at 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 https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Date shown on page March 10, 1971. December 29, 1970. Issued in Renton, Washington, on February 2, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–2416 Filed 2–13–07; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\14FER1.SGM 14FER1

Agencies

[Federal Register Volume 72, Number 30 (Wednesday, February 14, 2007)]
[Rules and Regulations]
[Pages 6921-6922]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-2416]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26084; Directorate Identifier 2006-NM-063-AD; 
Amendment 39-14937; AD 2007-04-06]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-62, DC-8-
63, DC-8-62F, and DC-8-63F 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 McDonnell Douglas Model DC-8-62, DC-8-63, DC-8-62F, and DC-8-
63F airplanes. This AD requires revising the wiring for the engine 
thrust brake circuit and indicating circuit and other specified 
actions, or rerouting the wiring at plug P1-1762A on the electrical 
power center generator control panel, as necessary. This AD results 
from the determination that the thrust reverser systems on these 
airplanes do not adequately preclude inadvertent deployment of the 
thrust reversers. We are issuing this AD to prevent inadvertent 
deployment of the thrust reversers during takeoff or landing, which 
could result in loss of control of the airplane.

DATES: This AD becomes effective March 21, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 21, 
2007.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024), for service information 
identified in this AD.

FOR FURTHER INFORMATION CONTACT: William Bond, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5253; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at https://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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain McDonnell 
Douglas Model DC-8-62, DC-8-63, DC-8-62F, and DC-8-63F airplanes. That 
NPRM was published in the Federal Register on October 19, 2006 (71 FR 
61690). That NPRM proposed to require revising the wiring for the 
engine thrust brake circuit and indicating circuit and other specified 
actions, or rerouting the wiring at plug P1-1762A on the electrical 
power center generator control panel, as necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 70 airplanes of the affected design in the 
worldwide fleet. This AD affects about 45 airplanes of U.S. registry. 
The required actions take between 1 and 5 work hours per airplane, 
depending on airplane configuration, at an average labor rate of $80 
per work hour. For a certain airplane configuration, required parts 
cost about $9 per airplane. For a certain other airplane configuration, 
required parts cost about $2,825 per airplane. Based on these figures, 
the estimated cost of this AD for U.S. operators is between $4,005 and 
$145,125, or between $89 and $3,225 per airplane.

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

[[Page 6922]]

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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2007-04-06 McDonnell Douglas: Amendment 39-14937. Docket No. FAA-
2006-26084; Directorate Identifier 2006-NM-063-AD.

Effective Date

    (a) This AD becomes effective March 21, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-8-62 and DC-8-
63 airplanes and Model DC-8-62F and DC-8-63F airplanes, certificated 
in any category; as identified in McDonnell Douglas DC-8 Service 
Bulletin 78-95, Revision 2, dated March 10, 1971.

Unsafe Condition

    (d) This AD results from the determination that the thrust 
reverser systems on McDonnell Douglas Model DC-8-62, DC-8-63, DC-8-
62F, and DC-8-63F airplanes do not adequately preclude inadvertent 
deployment of the thrust reversers. We are issuing this AD to 
prevent inadvertent deployment of the thrust reversers during 
takeoff or landing, which could result in loss of control of the 
airplane.

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.

Modification of Engine Thrust Brake Circuitry

    (f) Within 27 months after the effective date of this AD, do the 
applicable action specified in paragraph (f)(1) or (f)(2) of this 
AD, by accomplishing all of the applicable actions specified in the 
Accomplishment Instructions of McDonnell Douglas DC-8 Service 
Bulletin 78-95, Revision 2, dated March 10, 1971; or Revision 1, 
dated December 29, 1970.
    (1) Revise the wiring for the engine thrust brake circuit and 
indicating circuit, and do all other specified actions before 
further flight after revising the wiring.
    (2) Reroute the wiring at plug P1-1762A on the electrical power 
center generator control panel.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, Los Angeles Aircraft Certification Office, 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Material Incorporated by Reference

    (h) You must use McDonnell Douglas DC-8 Service Bulletin 78-95, 
Revision 2, dated March 10, 1971; or McDonnell Douglas DC-8 Service 
Bulletin 78-95, Revision 1, dated December 29, 1970; to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. McDonnell Douglas DC-8 Service Bulletin 78-95, Revision 
2, dated March 10, 1971, contains the following effective pages:

------------------------------------------------------------------------
                                  Revision
          Page number            level shown      Date shown on page
                                   on page
------------------------------------------------------------------------
1, 2, 16, 17..................            2   March 10, 1971.
3-15, 18-23...................            1   December 29, 1970.
------------------------------------------------------------------------

    The Director of the Federal Register approved the incorporation 
by reference of these documents in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach 
Division, 3855 Lakewood Boulevard, Long Beach, California 90846, 
Attention: Data and Service Management, Dept. C1-L5A (D800-0024), 
for a copy of this service information. You may review copies at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; 
on the Internet at https://dms.dot.gov; or at 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 https://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.

    Issued in Renton, Washington, on February 2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-2416 Filed 2-13-07; 8:45 am]
BILLING CODE 4910-13-P

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