Airworthiness Directives; Boeing Model 767-400ER, 777-200, and 777-300 Series Airplanes, 2064-2066 [05-614]

Download as PDF 2064 Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by February 28, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all McDonnell Douglas Model DC–10–10, DC–10–10F, DC– 10–15, DC–10–30, DC–10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD–10– 10F, MD–10–30F, MD–11, and MD–11F airplanes; certificated in any category. Unsafe Condition (d) This AD was prompted by reports of blocked drain holes of the pitot tubes. We are issuing this AD to prevent blocked drain holes of the pitot tubes, which could result in the accumulation of water in the pitotstatic system and consequent failure of that system. Failure of the pitot-static system could result in erroneous airspeed indications in the cockpit and consequent loss of airspeed control. AD. The forced air check must be done by certificated maintenance personnel. Note 3: Exercise care in checking pitot tubes to prevent severe burns to your hands. (1) Make certain that the pitot heat is off and the pitot tubes are not hot. Note 4: Excessive, as well as sudden, pressurization or depressurization applied to a pitot system by either method can cause damage to instruments. Do not exceed 9.0 pounds per square inch (psi) or 550 knots when pressurizing the system. Do not exceed 1.0 psi per second or 90 knots per second when pressurizing or depressurizing the system. (2) Three methods are given in Table 1 of this AD. Only one test must be done and all are equivalent. TABLE 1.—THREE TEST METHODS Method Description (i) 1 ................. (A) Install a 9/16 inch (14 millimeter (mm)) inner diameter hose approximately three feet (1 meter) long to the end of the pitot tube; and (B) Use the hose to carefully blow air (using your mouth) into the pitot tube. (A) Connect an air pressure source (dry Nitrogen) to the pitot tubes; and (B) Adjust the pressure source to 5-psi maximum. (A) Connect a pitot static test set; and (B) Adjust it to 450 knots at 0-feet altitude maximum. 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. Repetitive Inspections (f) Within 90 days after the effective date of this AD, do a detailed inspection for accumulation of debris (blockage) of the drain holes of the pitot tubes in accordance with paragraphs (g) and (h) of this AD. The actions required by paragraph (g) must be done before those in paragraph (h) of this AD. Repeat the inspection thereafter at intervals not to exceed 650 flight hours. Note 1: For the purposes of this AD, a detailed inspection is ‘‘an intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.’’ Visual Check (g) Do a visual check in accordance with paragraphs (g)(1) through (g)(3) of this AD. The visual check must be done by certificated maintenance personnel. (1) Make certain that the pitot heat is off and the pitot tubes are not hot. Note 2: Caution. Exercise care in checking pitot tubes to prevent severe burns to your hands. (2) Attempt to look through the left and right drain holes of each pitot tube. (3) Make sure that ambient light (or flashlight) is visible through both drain holes of each pitot tube. Forced Air Check (h) Do a forced air check in accordance with paragraphs (h)(1) through (h)(3) of this VerDate jul<14>2003 17:43 Jan 11, 2005 Jkt 205001 (ii) 2 ................ (iii) 3 ............... (3) Check for airflow out of each drain hole. Make sure that you do not cover the drain holes when checking. Special Test Equipment (i) If test method 3 in paragraph (h)(2)(iii) of this AD is used, an air data line tester with pitot and static port adapters is required. Corrective Action (j) If any evidence of drain hole blockage (e.g., air exiting from any pitot drain hole cannot be felt on the hand) is found during any inspection required by paragraph (f), (g), or (h) of this AD, before further flight, clean the hole in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. Chapter 34–11–02 of the applicable Boeing airplane maintenance manual is one approved method. Alternative Methods of Compliance (AMOCs) (k) The Manager, Los Angeles ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 Issued in Renton, Washington, on December 30, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–615 Filed 1–11–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20026; Directorate Identifier 2004–NM–150–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–400ER, 777–200, and 777– 300 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 767–400ER, 777– 200, and 777–300 series airplanes. This proposed AD would require replacing, with new parts, the existing tie-down fitting studs that secure galleys, purser work stations, and closets to the seat tracks. This proposed AD is prompted by a report that tie-down fitting studs were found damaged. We are proposing this AD to prevent a galley, purser work station, or closet from detaching from the tie-down fitting studs during an emergency landing, which could injure passengers or crewmembers, or obstruct escape routes and impede emergency evacuation. We must receive comments on this proposed AD by February 28, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW, Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: E:\FR\FM\12JAP1.SGM 12JAP1 Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules For service information identified in this proposed AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this 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, room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 20026; the directorate identifier for this docket is 2004–NM–150–AD. FOR FURTHER INFORMATION CONTACT: Robert Kaufman, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6433; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20026; Directorate Identifier 2004–NM–150–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that website, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review DOT’s complete Privacy Act Statement in the Federal Register 2065 published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. intended to adequately address the unsafe condition. Examining the Docket You can examine the 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and Service Information.’’ Discussion We have received a report indicating that tie-down fitting studs, which secure galleys, purser work stations, and closets to the seat tracks, have been found cracked or deformed on a Boeing 777–200 series airplane during production. Investigation revealed that the original torque values were too high, which damaged the fitting studs during installation. This condition, if not corrected, could result in a galley, purser work station, or closet detaching from the tie-down fitting studs during an emergency landing, which could injure passengers or crewmembers, or obstruct escape routes and impede emergency evacuation. The subject tie-down fitting studs were also installed on Boeing Model 767–400ER and 777–300 series airplanes using the same original torque values used on Model 777–200 series airplanes. Therefore, all of these models may be subject to the same unsafe condition. Relevant Service Information We have reviewed Boeing Service Bulletins 767–25–0338, dated October 9, 2003; and 777–25–0217, dated July 17, 2003. Those service bulletins describe procedures for replacing, with new parts, the existing tie-down fitting studs that secure galleys, purser work stations, and floor-mounted closets to the seat tracks. Accomplishing the actions specified in the service information is FAA’s Determination and Requirements of the Proposed AD Differences Between the Proposed AD and Service Information The compliance time for the actions that would be required by the proposed AD differs from the compliance times recommended in the service information. Boeing Service Bulletin 767–25–0338 recommends doing the actions ‘‘at the next maintenance period when manpower and facilities are available.’’ Boeing Service Bulletin 777– 25–0217 recommends doing the actions at the ‘‘next convenient maintenance opportunity, not to exceed 7 years from the initial release’’ of the service bulletin. In developing an appropriate compliance time for this AD, we considered the manufacturer’s recommendation, the degree of urgency associated with the subject unsafe condition, and the time necessary to perform the proposed actions. In light of all of these factors, we find that a 60month compliance time represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety. We have coordinated this difference with Boeing, and they concur with our proposed compliance time. Costs of Compliance There are about 349 airplanes of the affected design in the worldwide fleet, including about 118 U.S.-registered airplanes. The following table provides the estimated costs for U.S. operators to comply with this proposed AD, at an average labor rate of $65 per hour. ESTIMATED COSTS Work hours (for U.S.-registered airplanes) Airplane model 767–400ER ................................................................ 777–200 and –300 ..................................................... 1 Depending VerDate jul<14>2003 10 1 6–30 No. of U.S.registered airplanes Parts Cost per airplane $6,221 1,464–19,761 $6,871 1,854–21,711 on configuration. 17:43 Jan 11, 2005 Jkt 205001 PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 E:\FR\FM\12JAP1.SGM 12JAP1 6 118 Fleet cost $41,226 218,772–2,561,898 2066 Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 proposed 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: VerDate jul<14>2003 17:43 Jan 11, 2005 Jkt 205001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Issued in Renton, Washington, on December 30, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–614 Filed 1–11–05; 8:45 am] Boeing: Docket No. FAA–2005–20026; Directorate Identifier 2004–NM–150–AD. BILLING CODE 4910–13–P Comments Due Date DEPARTMENT OF TRANSPORTATION (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by February 28, 2005. Federal Aviation Administration Affected ADs 14 CFR Part 39 [Docket No. 2000–NM–168–AD] (b) None. Applicability RIN 2120–AA64 (c) This AD applies to Boeing Model 767– 400ER series airplanes, certificated in any category, having Variable Numbers VQ071 through VQ076 inclusive; and Model 777– 200 and –300 series airplanes, certificated in any category, as listed in Boeing Service Bulletin 777–25–0217, dated July 17, 2003. Airworthiness Directives; McDonnell Douglas Model DC–9–81 (MD–81), DC– 9–82 (MD–82), DC–9–83 (MD–83), DC– 9–87 (MD–87), and MD–88 Airplanes Unsafe Condition (d) This AD was prompted by a report that tie-down fitting studs were found damaged. We are issuing this AD to prevent a galley, purser work station, or closet from detaching from the tie-down fitting studs during an emergency landing, which could injure passengers or crewmembers, or obstruct escape routes and impede emergency evacuation. 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. Replacement (f) Within 60 months after the effective date of this AD: Replace, with new parts, the existing tie-down fitting studs that secure galleys, purser work stations, and floormounted closets to the seat tracks, by doing all actions in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767–25–0338, dated October 9, 2003 (for Boeing Model 767–400ER series airplanes); or Boeing Service Bulletin 777– 25–0217, dated July 17, 2003 (for Boeing Model 777–200 and –300 series airplanes); as applicable. Replacements Accomplished According to Previous Issue of Service Bulletin (g) For Boeing Model 777–200 and –300 series airplanes: Replacements accomplished before the effective date of this AD according to Boeing Service Bulletin 777–25–0217, dated July 18, 2002, are considered acceptable for compliance with the corresponding action specified in this AD. Alternative Methods of Compliance (AMOCs) (h) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 Federal Aviation Administration, DOT. ACTION: Proposed rule; withdrawal. AGENCY: SUMMARY: This action withdraws a notice of proposed rulemaking (NPRM) that proposed a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–87), and MD– 88 airplanes. That action would have required installing shield assemblies for power feeder cables in the forward and aft lower cargo compartments, and installing an additional shield for the power feeder cable of the auxiliary power unit in the aft lower cargo compartment. Since the issuance of the NPRM, the Federal Aviation Administration (FAA) has determined that the proposed requirements are included in the requirements of another existing AD; the NPRM does not contain any new requirements beyond those of the existing AD. Accordingly, the proposed rule is withdrawn. FOR FURTHER INFORMATION CONTACT: Elvin K. Wheeler, Aerospace Engineer, Systems and Equipment Branch, ANM– 130L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5344; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to add a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC–9–81 (MD–81), DC– 9–82 (MD–82), DC–9–83 (MD–83), DC– 9–87 (MD–87), and MD–88 airplanes; was published in the Federal Register as a notice of proposed rulemaking (NPRM) on October 30, 2003 (68 FR E:\FR\FM\12JAP1.SGM 12JAP1

Agencies

[Federal Register Volume 70, Number 8 (Wednesday, January 12, 2005)]
[Proposed Rules]
[Pages 2064-2066]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-614]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20026; Directorate Identifier 2004-NM-150-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 767-400ER, 777-200, and
777-300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 767-400ER, 777-200, and 777-300 series
airplanes. This proposed AD would require replacing, with new parts,
the existing tie-down fitting studs that secure galleys, purser work
stations, and closets to the seat tracks. This proposed AD is prompted
by a report that tie-down fitting studs were found damaged. We are
proposing this AD to prevent a galley, purser work station, or closet
from detaching from the tie-down fitting studs during an emergency
landing, which could injure passengers or crewmembers, or obstruct
escape routes and impede emergency evacuation.

DATES: We must receive comments on this proposed AD by February 28,
2005.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW, Nassif Building, room PL-401,
Washington, DC 20590.
By fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW, Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.

[[Page 2065]]

For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this 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, room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-20026; the directorate identifier for this docket is
2004-NM-150-AD.

FOR FURTHER INFORMATION CONTACT: Robert Kaufman, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 917-6433; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20026;
Directorate Identifier 2004-NM-150-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that website, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.

Examining the Docket

You can examine the 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.

Discussion

We have received a report indicating that tie-down fitting studs,
which secure galleys, purser work stations, and closets to the seat
tracks, have been found cracked or deformed on a Boeing 777-200 series
airplane during production. Investigation revealed that the original
torque values were too high, which damaged the fitting studs during
installation. This condition, if not corrected, could result in a
galley, purser work station, or closet detaching from the tie-down
fitting studs during an emergency landing, which could injure
passengers or crewmembers, or obstruct escape routes and impede
emergency evacuation.
The subject tie-down fitting studs were also installed on Boeing
Model 767-400ER and 777-300 series airplanes using the same original
torque values used on Model 777-200 series airplanes. Therefore, all of
these models may be subject to the same unsafe condition.

Relevant Service Information

We have reviewed Boeing Service Bulletins 767-25-0338, dated
October 9, 2003; and 777-25-0217, dated July 17, 2003. Those service
bulletins describe procedures for replacing, with new parts, the
existing tie-down fitting studs that secure galleys, purser work
stations, and floor-mounted closets to the seat tracks. Accomplishing
the actions specified in the service information is intended to
adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the Proposed AD and Service Information.''

Differences Between the Proposed AD and Service Information

The compliance time for the actions that would be required by the
proposed AD differs from the compliance times recommended in the
service information. Boeing Service Bulletin 767-25-0338 recommends
doing the actions ``at the next maintenance period when manpower and
facilities are available.'' Boeing Service Bulletin 777-25-0217
recommends doing the actions at the ``next convenient maintenance
opportunity, not to exceed 7 years from the initial release'' of the
service bulletin. In developing an appropriate compliance time for this
AD, we considered the manufacturer's recommendation, the degree of
urgency associated with the subject unsafe condition, and the time
necessary to perform the proposed actions. In light of all of these
factors, we find that a 60-month compliance time represents an
appropriate interval of time for affected airplanes to continue to
operate without compromising safety. We have coordinated this
difference with Boeing, and they concur with our proposed compliance
time.

Costs of Compliance

There are about 349 airplanes of the affected design in the
worldwide fleet, including about 118 U.S.-registered airplanes. The
following table provides the estimated costs for U.S. operators to
comply with this proposed AD, at an average labor rate of $65 per hour.

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Work hours
(for U.S.- Cost per No. of U.S.-
Airplane model registered Parts airplane registered Fleet cost
airplanes) airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
767-400ER.......................................................... 10 $6,221 $6,871 6 $41,226
777-200 and -300................................................... \1\ 6-30 1,464-19,761 1,854-21,711 118 218,772-2,561,898
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Depending on configuration.

[[Page 2066]]

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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed 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, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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]

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

Boeing: Docket No. FAA-2005-20026; Directorate Identifier 2004-NM-
150-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by February 28, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 767-400ER series airplanes,
certificated in any category, having Variable Numbers VQ071 through
VQ076 inclusive; and Model 777-200 and -300 series airplanes,
certificated in any category, as listed in Boeing Service Bulletin
777-25-0217, dated July 17, 2003.

Unsafe Condition

(d) This AD was prompted by a report that tie-down fitting studs
were found damaged. We are issuing this AD to prevent a galley,
purser work station, or closet from detaching from the tie-down
fitting studs during an emergency landing, which could injure
passengers or crewmembers, or obstruct escape routes and impede
emergency evacuation.

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.

Replacement

(f) Within 60 months after the effective date of this AD:
Replace, with new parts, the existing tie-down fitting studs that
secure galleys, purser work stations, and floor-mounted closets to
the seat tracks, by doing all actions in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-25-0338,
dated October 9, 2003 (for Boeing Model 767-400ER series airplanes);
or Boeing Service Bulletin 777-25-0217, dated July 17, 2003 (for
Boeing Model 777-200 and -300 series airplanes); as applicable.

Replacements Accomplished According to Previous Issue of Service
Bulletin

(g) For Boeing Model 777-200 and -300 series airplanes:
Replacements accomplished before the effective date of this AD
according to Boeing Service Bulletin 777-25-0217, dated July 18,
2002, are considered acceptable for compliance with the
corresponding action specified in this AD.

Alternative Methods of Compliance (AMOCs)

(h) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.

Issued in Renton, Washington, on December 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-614 Filed 1-11-05; 8:45 am]
BILLING CODE 4910-13-P

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