Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations 31131

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:

2001–11–11 Boeing: Amendment 39–12254.

Docket 2000–NM–156–AD.

Applicability: Model 737, 747, and 777

series airplanes; certificated in any category;

as specified in the Boeing service bulletins

listed in Table 1. below:

TABLE 1.—APPLICABILITY

For Model 737 series

airplanes.

737–25–1371, Revision 2, dated December 9, 1999;

For Model 737 series

airplanes.

737–25–1407, dated

December 9, 1999;

For Model 747 series

airplanes.

747–25–3196, Revision 1, dated May

13, 1999; or

For Model 777 series

airplanes.

777–25–0111, Revision 1, dated December 13, 1999;

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 (b) 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 unrestrained movement of the

passenger seats during high forward

deceleration of the airplane, which could

result in injury to the passengers or crew

members during an emergency landing,

accomplish the following:

Replacement

(a) Within 18 months after the effective

date of this AD: Replace all the seat track

fittings on all the passenger seats with new,

improved fittings, in accordance with the

Accomplishment Instructions specified in

Boeing Service Bulletin 737–25–1371;

Revision 2 or 737–25–1407, both dated

December 9, 1999 (for Model 737 series

airplanes); Boeing Service Bulletin 747–25–

3196, Revision 1, dated May 13, 1999 (for

Model 747 series airplanes); or Boeing

Service Bulletin 777–25–0111, Revision 1,

dated May 13, 1999 (for Model 777 series

airplanes); as applicable.

Alternative Methods of Compliance

(b) 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, Seattle

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(c) 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

(d) The replacement shall be done in

accordance with Boeing Service Bulletin

737–25–1371, Revision 2, dated December 9,

1999; Boeing Service Bulletin 737–25–1407,

dated December 9, 1999; Boeing Service

Bulletin 747–25–3196, Revision 1, dated May

13, 1999; or Boeing Service Bulletin 777–25–

0111, Revision 1, dated May 13, 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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. 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.

Effective Date

(e) This amendment becomes effective on

July 16, 2001.

Issued in Renton, Washington, on May 25,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–13998 Filed 6–8–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–350–AD; Amendment

39–12250; AD 2001–11–08]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400, 747–400F, 757–200,

757–200CB, 757–200PF, 767–200, 767–

300, and 767–300F Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 747–

400, 757–200, 767–200, and 767–300

series airplanes, that currently requires

repetitive checks to detect certain

failures in the warning electronic unit

(WEU) or modular avionic warning

electronic assembly (MAWEA);

repetitive tests to detect any failure of

tactile, visual, or aural alerts generated

by the WEU or MAWEA; and corrective

action, if necessary. This amendment

makes these requirements applicable to

other airplanes on which the defective

power supplies may be installed,

eliminates the repetitive tests for certain

airplanes, and increases the interval for

the repetitive tests for certain other

airplanes. This amendment also requires

replacing any subject power supply in

the WEU or MAWEA with a new,

modified, or serviceable power supply.

The actions specified by this AD are

intended to prevent failure of the WEU

or MAWEA power supplies, which

could result in loss of visual, aural, and

tactile alerts to the flightcrew. Absence

of such alerts could result in the

flightcrew being unaware that an

immediate or appropriate action should

be taken in the event of an unsafe

condition.

DATES: Effective July 16, 2001.

The incorporation by reference of

certain publications, as listed in the

regulations, is approved by the Director

of the Federal Register as of July 16,

2001.

The incorporation by reference of

certain other publications, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of September 16, 1999 (64 FR

47653, September 1, 1999).

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:

Sheila I. Mariano, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2675; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

31132 Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations

Aviation Regulations (14 CFR part 39)

by superseding AD 99–18–16,

amendment 39–11282 (64 FR 47653,

September 1, 1999), applicable to

certain Boeing Model 747–400, 757–

200, 767–200, and 767–300 series

airplanes, was published in the Federal

Register on June 15, 2000 (65 FR 37494).

That action proposed to continue to

require the actions specified in AD 99–

18–16, and to add a terminating action

for the repetitive checks and tests. That

action also proposed to make those

requirements applicable to other

airplanes on which the defective power

supplies may be installed, eliminate the

repetitive tests for certain airplanes, and

increase the interval for the repetitive

tests for certain other airplanes.

Additionally, that action also proposed

to require replacement of any subject

power supply in the WEU or MAWEA

with a new, modified, or serviceable

power supply. That action was

prompted by a report of a MAWEA

power supply failure due to inadequate

over-voltage protection.

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.

Support for the Proposed AD

One commenter supports the actions

specified by the proposed AD. Four

other commenters state that they are

either not affected by the proposed AD

or are in compliance with the proposed

actions.

Request To Withdraw the Proposed AD

One commenter states that the FAA

should determine the number of power

supply modules, part number (P/N)

285T0035–201, currently installed on

airplanes. If the subject power supply

module is found, the FAA should

require a fleet check for part numbers

and serial numbers before requiring

fleetwide preflight checks. If the

manufacturer of the subject part

(Boeing) could identify which serial

numbers were produced and identify

the units that have been modified by

July 2000, there may be no need to issue

an AD. The FAA infers that the

commenter is requesting that the

proposed AD be withdrawn.

The FAA does not concur that the

proposed AD should be withdrawn. The

applicability of this AD limits the

requirements to only certain airplanes

on which the affected P/N is installed.

Airplanes not included in the

applicability are not subject to preflight

checks or the requirements of this AD.

Issuance of this AD is necessary to

require U.S. operators of airplanes with

the affected P/N installed to accomplish

the required actions.

Request To Clarify the Terminating

Action

One commenter requests that the FAA

clarify the terminating action required

by the proposed AD. The commenter

states that the intent of the proposed AD

is to replace all power supplies, P/N

285T0035–201, found on certain Model

747, 757, and 767 series airplanes and

those power supplies in stock. After

such replacement, no further repetitive

checks are required. However, the

proposed AD does not provide clear

direction to the terminating action.

Paragraphs (a) and (b) of the proposed

AD require ‘‘test and replacement’’

action per paragraph (c) or (f). If the

action in paragraph (c) or (f) is

terminated, operators are not required to

do the action required by paragraph (d)

or (e), which specify repetitive checks

(for Model 747–400 and -400F series

airplanes not listed in paragraph (a))

and repetitive checks and functional

tests (for Model 757 and 767 series

airplanes not listed in paragraph (b)).

The operator states that, even though it

has replaced the subject power supplies,

the proposed AD still requires the

repetitive checks (as specified in

paragraph (d) of the proposed AD), and

the repetitive checks and functional

tests (as specified in paragraph (e) of the

proposed AD). This creates an

unintended burden on operators.

The FAA clarifies that the actions

required by paragraphs (a), (b), and (c)

of this AD in the section, ‘‘Partial

Restatement of Requirements of AD 99–

18–16,’’ are included for operators that

have not already replaced the power

supplies. For those operators, the checks

and functional tests, as well as the

corrective actions, continue to be

required by this new AD. The

replacement action was not required by

AD 99–18–16. However, this new AD

requires replacement of any subject

power supplies within 1 year after the

effective date of this AD, as the

terminating action. Paragraphs (c)(1),

(c)(2), and (c)(3) of this AD, clearly state

that replacement of the subject power

supplies constitutes terminating action

for the requirements of this AD. In

addition, we point out that the actions

required by paragraphs (d) and (e) of

this AD only apply to airplanes not

subject to the requirements of

paragraphs (a) and (b). Paragraphs (d)

and (e) both specify that replacement

action terminates the repetitive checks

and tests specified by this AD. The FAA

has revised paragraph (f) of this final

rule to clarify that such replacement

terminates ‘‘the requirements of this

AD,’’ rather than ‘‘the repetitive

inspection requirements of this AD.’’

Request To Add an Inspection

Requirement

One commenter requests an

inspection of the power supply module

to identify the P/N installed at the next

‘‘A’’ check or 45 days (after the effective

date of this AD), whichever occurs

earlier, and repetitive inspections if

subject P/N 285T0035–201 is found.

The commenter contends that the first

action in paragraphs (d) and (e) of the

proposed AD is to check the status page

of the EICAS for any MAWEA or WEU

failures, which assumes that the subject

P/N is installed. However, the FAA

should clarify those paragraphs to

specify that operators first must

determine if a subject P/N is installed at

the next ‘‘A’’ check or 45 days (after the

effective date of this AD), whichever

occurs first. If a subject P/N is found,

then the proposed AD should require

repetitive checks (as specified in

paragraphs (d) and (e) of the proposed

AD). The commenter adds that there is

no assurance that the subject P/N has

not been subsequently installed on an

airplane that was modified per AD 99–

18–16.

The FAA does not concur with the

commenter’s request to require an

additional inspection to determine if a

subject P/N is installed. The

applicability statement and certain

paragraphs of this AD limit the required

actions to only certain airplanes

equipped with either a WEU or

MAWEA power supply having P/N

28T0035–201. Some operators should be

able to review their maintenance log

books to determine if the subject P/N

has been replaced. Therefore, it is not

necessary to add an inspection in

paragraphs (d) and (e) of this AD to

determine if a subject power supply is

installed.

Also, the repetitive checks required

by paragraphs (d) and (e) of this AD are

limited to only certain airplanes

equipped with either a WEU or

MAWEA power supply having P/N

285T0035–201, other than those

airplanes identified in paragraph (a) or

(b) of this AD. We have revised

paragraphs (d) and (e) of this AD

accordingly to clarify any confusion.

We do not agree that operators may

have inadvertently installed the subject

P/N on a previously modified airplane.

We point out that, for airplanes subject

to AD 99–18–16, paragraph (g) of that

AD specifies that no person shall install

a WEU or MAWEA power supply

having P/N 285T0035–201 on any

Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations 31133

airplane as of the effective date of that

AD, as specified in paragraph (g)(1) of

this AD. Therefore, no change to this AD

is necessary in this regard.

Requests To Correct a Paragraph

Reference

Two commenters request changing a

paragraph reference in paragraphs (d)(1)

and (e)(1) of the proposed AD. The

commenters state that the correct

paragraph reference for the terminating

action required by the proposed AD is

paragraph (f) instead of paragraph (e).

The FAA concurs with this request and

has changed the final rule accordingly.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 1,592 Model

747–400, 747–400F, 757–200, 757–

200CB, 757–200PF, 767–200, 767–300,

and 767–300F series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 802 airplanes of

U.S. registry will be affected by this AD.

The repetitive checks and tests

required by AD 99–18–16 are currently

applicable to approximately 33 U.S.-

registered airplanes. The repetitive

checks and tests take approximately 1

work hour per airplane to accomplish,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the currently required checks

and tests on U.S. operators is estimated

to be $1,980, or $60 per airplane, per

check/test cycle. Because this AD

eliminates the currently required

repetitive tests for certain airplanes, and

increases the repetitive interval for the

tests for certain other airplanes, this AD

reduces the costs to operators currently

subject to AD 99–18–16.

The repetitive checks and tests in this

new action are applicable to

approximately 769 additional airplanes.

Based on the figures discussed above,

the new costs to U.S. operators for the

repetitive checks and tests imposed by

this AD are estimated to be $46,140, or

$60 per airplane, per check/test cycle.

For all airplanes subject to this AD,

the new replacement action required by

this AD takes approximately 3 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Required parts cost approximately

$6,424 per airplane. Based on these

figures, the cost impact of the

replacement required by this AD on U.S.

operators is estimated to be $5,296,408,

or $6,604 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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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

removing 39–11282 (64 FR 47653,

September 1, 1999), and by adding a

new airworthiness directive (AD),

amendment 39–12250, to read as

follows:

2001–11–08 Boeing: Amendment 39–12250.

Docket 99-NM–350-AD. Supersedes AD

99–18–16, Amendment 39–11282.

Applicability: Model 747–400, 747–400F,

757–200, 757–200CB, 757–200PF, 767–200,

767–300, and 767–300F series airplanes;

equipped with either a warning electronics

unit (WEU) or a modular avionics warning

electronic assembly (MAWEA) power supply

having part number (P/N) 285T0035–201;

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 (h)(1) 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 WEU or MAWEA

power supplies, which could result in loss of

visual, aural, and tactile alerts to the

flightcrew (the absence of which could result

in the flightcrew being unaware that an

immediate or appropriate action should be

taken in the event of an unsafe condition),

accomplish the following:

Partial Restatement of Requirements of AD

99–18–16

Model 747–400 Series Airplanes: EICAS

Status Page Checks

(a) For Model 747–400 and 747–400F

series airplanes having line number (L/N)

1121 through 1177 inclusive: Within 15 days

after September 16, 1999 (the effective date

of AD 99–18–16, amendment 39–11282),

check the status page of the engine indication

and crew alerting system (EICAS) for any

MAWEA failure. Thereafter, repeat the

EICAS status page check before each flight

until the requirements of paragraph (c) or (f)

of this AD have been accomplished.

Model 757–200, 767–200, and 767–300 Series

Airplanes: Checks and Functional Tests

(b) For Model 757–200, –200CB, and

–200PF series airplanes having L/N 761

through 828 inclusive; and Model 767–200,

–300, and –300F series airplanes having L/N

668 through 723 inclusive: Within 15 days

after September 16, 1999, check the status

page of the EICAS for any WEU failure; and

perform the Work Instructions in Section 3,

31134 Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations

Part 1, of Boeing Service Bulletin 757–31–

0066, Revision 1, dated December 17, 1998,

or Revision 2, dated November 18, 1999 (for

Model 757–200, –200CB, and –200PF series

airplanes); or Boeing Service Bulletin 767–

31–0106, Revision 1, dated December 17,

1998, or Revision 2, dated November 18,

1999 (for Model 767–200, 767–300, and 767–

300F series airplanes); as applicable; to

detect loss of any visual, aural, or tactile

alert. Thereafter, repeat the EICAS status

page check before each flight, and the Work

Instructions in Section 3, Part 1, of the

applicable service bulletin at intervals not to

exceed every ‘‘A’’ check or 45 days,

whichever occurs first, until the

requirements of paragraph (c) or (f) of this AD

have been accomplished. After the effective

date of this AD, only Revision 2 of the

applicable service bulletin shall be used.

Corrective Action

(c) If any failure of the MAWEA or WEU,

as applicable, or the loss of any visual, aural,

or tactile alert is detected during any test

required by either paragraph (a) or (b) of this

AD, prior to further flight, accomplish

paragraph (c)(1), (c)(2), or (c)(3) of this AD;

as applicable.

(1) For Model 747–400 or –400F series

airplanes equipped with a MAWEA power

supply having P/N 285T0035–201: Replace

the power supplies of the MAWEA with new

or modified power supplies having P/N

285T0035–202 Mod A, in accordance with

either Boeing Service Bulletin 747–31–2288,

dated December 17, 1998, or Revision 1,

dated January 28, 1999; or with new,

modified, or serviceable power supplies

having P/N 285T0035–202 Mod A, P/N

285T0035–10, or P/N 285T0035–11, in

accordance with Boeing Service Bulletin

747–31–2288, Revision 2, dated November

18, 1999. Such replacement constitutes

terminating action for the requirements of

this AD. After the effective date of this AD,

only Revision 2 of the applicable service

bulletin shall be used.

Note 2: Page 59 of Boeing Service Bulletin

747–31–2288, Revision 1, dated January 28,

1999, incorrectly references the Boeing 767

AMM as the appropriate source of service

information for accomplishment of the

removal and installation of the power supply.

However, the correct reference is the Boeing

747 AMM.

(2) For Model 757–200, –200CB, and

–200PF series airplanes equipped with a

MAWEA power supply having P/N

285T0035–201: Replace the power supplies

of the WEU with new or modified power

supplies having P/N 285T0035–202 Mod A,

in accordance with Boeing Service Bulletin

757–31–0066, Revision 1, dated December

17, 1998; or with new, modified, or

serviceable power supplies having P/N

285T0035–202 Mod A, P/N 285T0035–9, P/

N 285T0035–10, or P/N 285T0035–11, in

accordance with Boeing Special Attention

Service Bulletin 757–31–0066, Revision 2,

dated November 18, 1999. Such replacement

constitutes terminating action for the

requirements of this AD. After the effective

date of this AD, only Revision 2 of the service

bulletin shall be used.

(3) For Model 767–200, –300, and –300F

series airplanes: Replace the power supplies

of the WEU with new or modified power

supplies having P/N 285T0035–202 Mod A,

in accordance with Boeing Service Bulletin

767–31–0106, Revision 1, dated December

17, 1998; or with new, modified, or

serviceable power supplies having P/N

285T0035–202 Mod A, P/N 285T0035–9, P/

N 285T0035–10, or P/N 285T0035–11, in

accordance with Boeing Special Attention

Service Bulletin 767–31–0106, Revision 2,

dated November 18, 1999. Such replacement

constitutes terminating action for the

requirements of this AD. After the effective

date of this AD, only Revision 2 of the

applicable service bulletin shall be used.

New Requirements of This AD

Note 3: Boeing Component Service Bulletin

285T0035–31–07, dated December 17, 1998,

describes procedures for modifying WEU or

MAWEA power supplies having P/N

28T0035–201 to 285T0035–202 Mod A.

Repetitive Checks: Model 747–400 and –400F

(d) For Model 747–400 and –400F series

airplanes equipped with a MAWEA power

supply having P/N 28T0035–201, other than

those airplanes identified in paragraph (a) of

this AD: At the next ‘‘A’’ check or within 45

days, whichever occurs first, check the status

page of the EICAS for any MAWEA failure.

(1) If no MAWEA failure is detected:

Thereafter, repeat the EICAS status page

check before each flight, until the

requirements of paragraph (f) of this AD are

accomplished.

(2) If any MAWEA failure is detected: Prior

to further flight, replace MAWEA power

supplies having P/N 285T0035–201 with new

or modified power supplies having P/N

285T0035–202 Mod A, or new, modified, or

serviceable power supplies having P/N

285T0035–10 or P/N 285T0035–11; in

accordance with Boeing Service Bulletin

747–31–2288, Revision 2, dated November

18, 1999. Such replacement constitutes

terminating action for the requirements of

this AD.

Repetitive Checks and Functional Tests:

Model 757 and 767

(e) For Model 757–200, 757–200CB, 757–

200PF, 767–200, 767–300, and 767–300F

series airplanes equipped with a WEU power

supply having P/N 28T0035–201, other than

those airplanes identified in paragraph (b) of

this AD: At the next ‘‘A’’ check or within 45

days, whichever occurs first, check the status

page of the EICAS for any WEU failure; and

perform the Work Instructions in Section 3,

Part 1, of Boeing Special Attention Service

Bulletin 757–31–0066, Revision 2, dated

November 18, 1999; or Boeing Special

Attention Service Bulletin 767–31–0106,

Revision 2, dated November 18, 1999; as

applicable; to detect loss of any visual, aural,

or tactile alert.

(1) If no failure of the WEU or loss of any

visual, aural, or tactile alert is detected:

Thereafter, repeat the EICAS status page

check before each flight, and accomplish the

Work Instructions in Section 3, Part 1 of the

applicable service bulletin at intervals not to

exceed every ‘‘A’’ check or 45 days,

whichever occurs first, until the

requirements of paragraph (f) of this AD are

accomplished.

(2) If any failure of the WEU or loss of any

visual, aural, or tactile alert is detected: Prior

to further flight, replace WEU power supplies

having P/N 285T0035–201, with new or

modified power supplies having P/N

285T0035–202 Mod A; or new, modified, or

serviceable power supplies having P/N

285T0035–9, P/N 285T0035–10, or P/N

285T0035–11; in accordance with the

applicable service bulletin. Such replacement

constitutes terminating action for the

requirements of this AD.

Replacement

(f) Within 1 year after the effective date of

this AD, replace WEU or MAWEA power

supplies having P/N 285T0035–201, with

new or modified power supplies having P/N

285T0035–202 Mod A; or new, modified, or

serviceable power supplies having P/N

285T0035–9, P/N 285T0035–10, or P/N

285T0035–11; in accordance with Boeing

Service Bulletin 747–31–2288, dated

December 17, 1998, Revision 1, dated January

28, 1999, or Revision 2, dated November 18,

1999 (for Model 747–400 and 747–400F

series airplanes); Boeing Service Bulletin

757–31–0066, Revision 1, dated December

17, 1998, or Revision 2, dated November 18,

1999 (for Model 757–200, 757–200CB, and

757–200PF series airplanes); or Boeing

Service Bulletin 767–31–0106, Revision 1,

dated December 17, 1998, or Revision 2,

dated November 18, 1999 (for Model 767–

200, 767–300, and 767–300F series

airplanes); as applicable. After the effective

date of this AD, only Revision 2 of the

applicable service bulletin shall be used.

Such replacement constitutes terminating

action for the requirements of this AD.

Spares

(g) As of the date specified in paragraph

(g)(1) or (g)(2) of this AD, as applicable, no

person shall install a WEU or MAWEA power

supply having Boeing P/N 285T0035–201 on

any airplane.

(1) For Model 747–400 series airplanes,

line numbers 1121 through 1177 inclusive;

Model 757–200, –200CB, and –200PF series

airplanes, line numbers 761 through 828

inclusive; and Model 767–200, 767–300, and

–300F series airplanes, line numbers 668

through 723 inclusive: As of September 16,

1999 (the effective date of AD 99–18–16,

amendment 39–11282).

(2) For airplanes other than those

identified in paragraph (g)(1) of this AD: As

of the effective date of this AD.

Alternative Methods of Compliance

(h)(1) 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, Seattle

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Avionics

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

(2) Alternative methods of compliance,

approved previously by the FAA in

accordance with AD 99–18–16, amendment

39–11282, are approved as alternative

methods of compliance with this AD.

Note 4: Information concerning the

existence of approved alternative methods of

Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations 31135

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(i) 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

(j) Except for the EICAS status page checks

required by paragraphs (a), (b), (d), (d)(1), (e),

and (e)(1) of this AD, the actions shall be

done in accordance with Boeing Service

Bulletin 747–31–2288, dated December 17,

1998; Boeing Service Bulletin 747–31–2288,

Revision 1, dated January 28, 1999; Boeing

Service Bulletin 747–31–2288, Revision 2,

including Appendix A, dated November 18,

1999; Boeing Service Bulletin 757–31–0066,

Revision 1, dated December 17, 1998; Boeing

Special Attention Service Bulletin 757–31–

0066, Revision 2, including Appendix A,

dated November 18, 1999; Boeing Service

Bulletin 767–31–0106, Revision 1, dated

December 17, 1998; or Boeing Special

Attention Service Bulletin 767–31–0106,

Revision 2, including Appendix A, dated

November 18, 1999; as applicable.

(1) The incorporation by reference of

Boeing Service Bulletin 747–31–2288,

Revision 2, including Appendix A, dated

November 18, 1999; Boeing Special Attention

Service Bulletin 757–31–0066, Revision 2,

including Appendix A, dated November 18,

1999; and Boeing Special Attention Service

Bulletin 767–31–0106, Revision 2, including

Appendix A, dated November 18, 1999; is

approved by the Director of the Federal

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

and 1 CFR part 51.

(2) The incorporation by reference of

Boeing Service Bulletin 747–31–2288, dated

December 17, 1998; Boeing Service Bulletin

747–31–2288, Revision 1, dated January 28,

1999; Boeing Service Bulletin 757–31–0066,

Revision 1, dated December 17, 1998; and

Boeing Service Bulletin 767–31–0106,

Revision 1, dated December 17, 1998; was

approved previously by the Director of the

Federal Register as of September 16, 1999 (64

FR 47653, September 1, 1999).

(3) Copies may be obtained from Boeing

Commercial Airplane Group, P.O. Box 3707,

Seattle, Washington 98124–2207. 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.

Effective Date

(k) This amendment becomes effective on

July 16, 2001.

Issued in Renton, Washington, on May 25,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–13999 Filed 6–8–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–298–AD; Amendment

39–12249; AD 2001–11–07]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737, 757, and 767 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 737,

757, and 767 series airplanes. This AD

requires repetitive operational checks of

certain motor-operated hydraulic

shutoff valves to detect malfunctioning;

replacement with new valves, if

necessary; and eventual replacement of

certain existing valves with new valves,

which terminates the repetitive

inspections. This amendment is

prompted by reports that various

intermittent limit-switch problems have

caused valve failures. The actions

specified by this AD are intended to

prevent failure of the motor-operated

hydraulic shutoff valves, which could

result in leakage of hydraulic fluid to

the engine fire zone, reduced ability to

retract the landing gear, loss of backup

electrical power or other combinations

of failures; and consequent reduced

controllability of the airplane.

DATES: Effective July 16, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 16,

2001.

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:

Kenneth W. Frey, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2673; 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 737, 757, and 767 series

airplanes was published as a

supplemental notice of proposed

rulemaking (NPRM) in the Federal

Register on June 21, 2000 (65 FR 38450).

That action proposed to require

repetitive operational checks of certain

motor-operated hydraulic shutoff valves

to detect malfunctioning; replacement

with new valves, if necessary; and

eventual replacement of certain existing

valves with new valves, which

terminates 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.

Support for the Proposal

One commenter concurred with the

original notice of proposed rulemaking

(NPRM), and that commenter submitted

no additional comment to the

supplemental NPRM.

Request To Clarify Subject Valves

Several commenters request that the

FAA clarify the language in the original

NPRM and supplemental NPRM to

clarify what valves on the airplane are

subject to the proposed AD. The

commenters point out that the

referenced service bulletins apply only

to valves in ‘‘sensitive system’’

applications (hereinafter referred to as

‘‘sensitive’’ applications). However, the

language in the NPRM and

supplemental NPRM does not clarify

whether only valves with the subject

part numbers (P/N) in ‘‘sensitive’’

applications are subject to the

requirements of the proposed AD, or

whether ALL valves with the subject P/

N’s installed on the airplane are subject

to the proposed AD, regardless of

whether the valves are installed in

‘‘sensitive’’ or ‘‘non-sensitive’’

applications.

The FAA concurs with the

commenters’ request for clarification.

This AD is intended to apply only to the

valves in locations listed in the

referenced service bulletins—that is,

valves in ‘‘sensitive’’ applications. The

FAA has revised paragraphs (a) and (b)

of this AD accordingly and added a new

note, Note 1, after the applicability

statement to clarify this issue.

(Subsequent notes have also been

reordered.)

Operators should note that, while the

airplane manufacturer will issue new

service bulletins with instructions for