Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37019

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

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

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

2000–11–21 Airbus Industrie: Amendment

39–11769. Docket 99–NM–331–AD.

Applicability: The following models,

certificated in any category, excluding those

on which Airbus Service Bulletin A320–27–

1126, dated April 26, 1999 (for Model A319

and 321 series airplanes); or A320–27–1127,

dated April 26, 1999, or Revision 01, dated

October 6, 1999 (for Model A320 series

airplanes); has been accomplished:

• Model A319 series airplanes, serial

numbers (S/N) 0546 through 0972 inclusive;

• Model A320 series airplanes, S/N 0002

through 0842 inclusive, 0846 through 0859

inclusive, 0865, 0866, and 0872 through 0960

inclusive; and

• Model A321 series airplanes, S/N 0364

through 0974 inclusive.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For airplanes that have been modified,

altered, or repaired so that the performance

of the requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the servocontrol

piston rod, which could result in reduced

controllability of the airplane, accomplish

the following:

Inspection

(a) At the applicable time specified by

paragraph (a)(1) or (a)(2) of this AD: Perform

a general visual inspection to determine the

part number and serial number for the spoiler

servocontrols, in accordance with Airbus

Service Bulletin A320–27–1126, April 26,

1999, or Revision 01, dated October 6, 1999

(for Model A319 and A321 series airplanes);

or Airbus Service Bulletin A320–27–1127,

dated April 26, 1999, or Revision 01, dated

October 6, 1999 (for Model A320 series

airplanes); as applicable. If the part number

and serial number are identified in paragraph

2.B.(1)(b) of the Accomplishment

Instructions of the applicable service

bulletin, prior to further flight, perform

applicable corrective actions (including

removal, reidentification of the servocontrol,

and replacement of the servocontrol with a

modified part) as specified in the applicable

service bulletin.

(1) For Model A319 and A321 series

airplanes: Inspect within 2 months after the

effective date of this AD.

(2) For Model A320 series airplanes:

Inspect within 28 months after the effective

date of this AD.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Spares

(b) As of the effective date of this AD, no

person shall install on any airplane a spoiler

servocontrol having part number 31077–050,

31077–060, or 31077–110; and S/N 0001 to

3499, except those serial numbers excluded

in paragraph 2.B.(1)(b)1 of the

Accomplishment Instructions in Airbus

Service Bulletin A320–27–1126, dated April

26, 1999, or Revision 01, dated October 6,

1999; unless that servocontrol has been

inspected, and corrective actions have been

performed, in accordance with the

requirements of this AD.

Alternative Methods of Compliance

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The actions shall be done in accordance

with Airbus Service Bulletin

A320–27–1126, including Appendices 01

and 02, dated April 26, 1999; Airbus Service

Bulletin A320–27–1126, Revision 01

including Appendices 01 and 02, dated

October 6, 1999; Airbus Service Bulletin

A320–27–1127, including Appendices 01

and 02, dated April 26, 1999; or Airbus

Service Bulletin A320–27–1127, Revision 01

including Appendices 01 and 02, dated

October 6, 1999; as applicable. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: The subject of this AD is addressed

in French airworthiness directive 1999–362–

139(B), dated September 8, 1999.

(f) This amendment becomes effective on

July 18, 2000.

Issued in Renton, Washington, on June 1,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14311 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–128–AD; Amendment

39–11772; AD 2000–11–23]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A310, and A300–600 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A300,

A310, and A300–600 series airplanes,

that requires an inspection to detect

damage of the electrical bonding leads

in specified locations of the fuel tanks,

and replacement of any damaged

37020 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

electrical bonding leads with

serviceable electrical bonding leads. For

certain airplanes, this amendment also

requires modifying the fuel pipe

couplings in specified locations of the

fuel tank. This amendment is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent electrical arcing/

discharge in the fuel tank due to

damaged electrical bonding leads or

inadequate electrical bonding of the fuel

pipe couplings, which could result in

fuel ignition and consequent

uncontained rupture of the fuel tank.

DATES: Effective July 18, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 18,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Airbus Model

A300, A310, and A300–600 series

airplanes was published in the Federal

Register on March 27, 2000 (65 FR

16151). That action proposed to require

an inspection to detect damage of the

electrical bonding leads in specified

locations of the fuel tanks, and

replacement of any damaged electrical

bonding leads with serviceable

electrical bonding leads. For certain

airplanes, that action also proposed to

require modifying the fuel pipe

couplings in specified locations of the

fuel tank.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 116 airplanes

of U.S. registry will be affected by this

AD.

It will take between 70 and 80 work

hours per airplane to accomplish the

required inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

required inspection on U.S. operators is

estimated to be between $487,200 and

$556,800, or between $4,200 and $4,800

per airplane.

It will take between 77 and 103 work

hours per airplane to accomplish the

required modification, at an average

labor rate of $60 per work hour.

Required parts will cost approximately

$104 per airplane. Based on these

figures, the cost impact of the required

modification on U.S. operators is

estimated to be between $547,984 and

$728,944, or between $4,724 and $6,284

per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein 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. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

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

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

2000–11–23 Airbus Industrie: Amendment

39–11772. Docket 99–NM–128–AD.

Applicability: All Model A300, A310, and

A300–600 series airplanes, certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent electrical arcing/discharge in

the fuel tank due to damaged electrical

bonding leads or inadequate electrical

bonding of the fuel pipe couplings, which

could result in fuel ignition and consequent

uncontained rupture of the fuel tank,

accomplish the following:

Inspection

(a) Within 36 months after the effective

date of this AD, perform a one-time

inspection to detect damage (i.e., breakage,

fraying, abrasion damage, looseness of the

outer metal braid protection in the end

crimp, looseness of the outer metal braid

protection on the bonding lead inner core,

corrosion, or missing leads) of the electrical

bonding leads in specified locations of the

fuel tanks, in accordance with the

Accomplishment Instructions of Airbus

Service Bulletins A300–28–0072, Revision

01, dated October 01, 1998, including

Appendix 1, dated October 01, 1998, and

Appendix 2, dated February 20, 1998 (for

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37021

Model A300 series airplanes); A310–28–

2128, Revision 01, dated October 01, 1998,

including Appendix 1, dated October 01,

1998, and Appendix 2, dated February 20,

1998 (for Model A310 series airplanes); or

A300–28–6057, Revision 01, dated October

01, 1998, including Appendix 1, dated

October 01, 1998, and Appendix 2, dated

February 20, 1998 (for Model A300–600

series airplanes); as applicable.

Note 2: Inspection of the area specified in

paragraph (a) of this AD accomplished prior

to the effective date of this AD in accordance

with Airbus Service Bulletins A300–28–

0072, A310–28–2128, or A300–28–6057; all

dated February 20, 1998; as applicable; is

considered acceptable for compliance with

the requirements of paragraph (a) of this AD.

Replacement

(b) If any electrical bonding lead is

damaged, prior to further flight, replace the

bonding lead with a serviceable bonding lead

in accordance with the applicable service

bulletin specified in paragraph (a) of this AD.

Modification

(c) For airplanes on which Airbus Industrie

Modification 11847 (for Model A310 series

airplanes) or 11848 (for Model A300/A300–

600 series airplanes) has not been

accomplished, within 36 months after the

effective date of this AD, modify the fuel pipe

couplings in the specified locations of the

fuel tank in accordance with the

Accomplishment Instructions of Airbus

Service Bulletins A300–28–0073, Revision

01, dated October 01, 1998 (for Model A300

series airplanes); A310–28–2130, Revision

01, dated October 01, 1998 (for Model A310

series airplanes); or A300–28–6058, Revision

01, dated October 01, 1998 (for Model A300–

600 series airplanes); as applicable.

Note 3: Modification of the fuel pipe

couplings accomplished prior to the effective

date of this AD in accordance with Airbus

Service Bulletins A300–28–0073, A310–28–

2130, or A300–28–6058; all dated February

20, 1998; as applicable; is considered

acceptable for compliance with the

requirements of paragraph (c) of this AD.

Alternative Methods of Compliance

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(e) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(f) The actions shall be done in accordance

with the following Airbus service bulletins,

as applicable:

Service bulletin No. Page No. Revision level

shown on page

Date shown on

page

A300–28–0072, Revision 01, October 01, 1998 ....... 1–14 ........................................................................... 01 ..................... Oct. 01, 1998.

Appendix 1

1–21, 23–25, 27, 29–36, 38–84, 88–95, 97–166 ..... Original ............. Feb. 20, 1998.

22, 26, 28, 37, 85–87, 96 .......................................... 01 ..................... Oct. 01, 1998.

Appendix 2

1–54 ........................................................................... Original ............. Feb. 20, 1998.

A310–28–2128, Revision 01, October 01, 1998 ....... 1–14 ........................................................................... 01 ..................... Oct. 01, 1998.

Appendix 1

1–30, 32–83, 85–87, 89–95, 97–221, 223–226 ........ Original ............. Feb. 20, 1998.

31, 84, 88, 96, 222 .................................................... 01 ..................... Oct. 01, 1998.

Appendix 2

1–56 ........................................................................... Original ............. Feb. 20, 1998

A300–28–6057, Revision 01, October 01, 1998 1–14 ........................................................................... 01 ..................... Oct. 01, 1998.

Appendix 1

1–18, 21–25, 27–29, 31, 33, 34, 36, 38, 40, 42, 44–

78, 81–85, 87–89, 91, 93, 94, 96, 98–100, 102,

104–229, 231–234.

Original ............. Feb. 20, 1998.

19, 20, 26, 30, 32, 35, 37, 39, 41, 43, 79, 80, 86,

90, 92, 95, 97, 101, 103, 230.

01 ..................... Oct. 01, 1998.

Appendix 2

1–54 ........................................................................... Original ............. Feb. 20, 1998.

A300–28–0073, Revision 01, October 01, 1998 ....... 1–67 ........................................................................... 01 ..................... Oct. 01, 1998.

A310–28–2130, Revision 01, October 01, 1998 ....... 1–91 ........................................................................... 01 ..................... Oct. 01, 1998.

A300–28–6058, Revision 01, October 01, 1998 ....... 1–67 ........................................................................... 01 ..................... Oct. 01, 1998.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

37022 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 5: The subject of this AD is addressed

in French airworthiness directive 98–174–

248(B), dated April 22, 1998.

(g) This amendment becomes effective on

July 18, 2000.

Issued in Renton, Washington, on June 2,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14437 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–208–AD; Amendment

39–11777; AD 2000–11–28]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 and 767–200 and –300

Series Airplanes Powered by Pratt &

Whitney Model PW4000 Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747–

400 and 767–200 and –300 series

airplanes, that requires repetitive

inspections to detect damage and wear

of the auxiliary track assembly of the

thrust reverser, and corrective actions, if

necessary. This amendment also

requires eventual repair of the auxiliary

track assembly, or replacement of the

slider and liner or the entire assembly,

with new, improved parts, which, when

accomplished, would terminate the

repetitive inspections. This amendment

is prompted by reports of damage and

wear to the auxiliary track assembly.

The actions specified by this AD are

intended to prevent a slider disengaging

from the auxiliary track assembly,

which could lead to separation of a

portion of the thrust reverser from the

airplane during flight, possible impact

of separated portions on airplane

structure, and consequent possible rapid

decompression of the airplane, reduced

controllability of the airplane, or

reduced structural integrity of the

fuselage.

DATES: Effective July 18, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 18,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Sulmo Mariano, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Transport Airplane Directorate, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2686;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Boeing

Model 747–400 and 767–200 and –300

series airplanes was published in the

Federal Register on October 19, 1999

(64 FR 56276). That action proposed to

require repetitive inspections to detect

damage and wear of the auxiliary track

assembly of the thrust reverser, and

corrective actions, if necessary. That

action also proposed to require eventual

replacement of the liner and slider, or

the entire assembly, with new,

improved parts, which, when

accomplished, would terminate the

repetitive inspections.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter supports the

proposed rule.

Request To Revise Certain

Requirements in the Proposed AD

Several commenters indicate that they

disagree with the proposed replacement

of the auxiliary track beam assembly,

including installation of a new slider

and liner, regardless of the amount of

wear and/or damage to the track beam.

The commenters request that repair of

the track beam be allowed when the

damage is within the allowable limits

specified in the referenced service

information. One commenter states that

replacement of the track beam fitting is

required only when the wear or damage

is beyond repairable limits, as specified

in Boeing Service Bulletin 747–

78A2164, Revision 2, and Boeing

Service Bulletin 767–78A0079, Revision

2. The commenter notes that

replacement of the track beam fitting in

and of itself does nothing to address the

root cause of the excessive wear;

however, the new design slider fitting

and track liner do address and correct

the root cause. A second commenter

states that the service bulletins specify

replacement of the track beam assembly

if the track beam has any discrepancy

AND the measurement of the gap is

greater than 0.45 inch. If the track beam

has any discrepancy and the gap

measurement is less than 0.45 inch,

only the slider and liner should be

replaced. Another commenter states that

replacement of the track beam assembly

is necessary only when damage cannot

be repaired by means of replacement of

the liner, slider, and/or retainer bar.

The FAA concurs with the

commenters’ requests. The FAA has

coordinated this issue with the

manufacturer, and has determined that

if the damage to the track beam

assembly is not beyond the repairable

limits specified in the referenced service

bulletins, a repair that involves

replacement of the slider and liner and

installation of a retainer bar, in lieu of

replacement of the track beam assembly,

is acceptable. Therefore, paragraphs (a)

and (c) of this AD have been revised to

specify measuring the auxiliary track

beam dimensions in accordance with

the Accomplishment Instructions of the

referenced service bulletins, and to

allow repair if the measurement is

within the allowable limits.

Request To Revise Cost Impact

Information

One commenter states that the total

number of U.S.-registered Model 747–

400 series airplanes affected by the

proposed AD should be higher than the

12 airplanes shown in the cost impact

section. The commenter indicates that it

has 10 affected airplanes in its fleet and

assumes that other operators also have

Model 747–400 series airplanes that are

affected by the proposal.

The FAA concurs. The referenced

service bulletin specifies a total of 36

Model 747–400 series airplanes of U.S.-

registry that are powered by Pratt &

Whitney PW4000 series engines. In light

of this information, the FAA has revised

the cost impact information, below, to

specify that 36 Model 747–400 series

airplanes of U.S. registry will be affected

by this AD.

Request for Credit for Previously

Accomplished Work

One commenter requests credit for

prior accomplishment of work done in