Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules 10387

Model As listed in * * * Service bulletin date

737–600, –700, and –800 series ......................................... Boeing Special Attention Service Bulletin 737–25–1403 ... Do.

737–600, –700, and –800 series ......................................... Boeing Service Bulletin 737–25–1404 ............................... Do.

757–200 and –200CB series ............................................... Boeing Service Bulletin 757–25–0217 ............................... Do.

757–300 series ..................................................................... Boeing Service Bulletin 757–25–0218 ............................... Do.

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 (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 an escape slide to

deploy or inflate correctly, which could

result in the slide being unusable during an

emergency evacuation and consequent injury

to passengers or airplane crewmembers,

accomplish the following:

Modification

(a) At the schedule specified in the

following table, do the actions in the ‘‘Do

these actions * * * ’’ column, per the service

bulletin specified in the ‘‘As listed in * * *’’

column:

TABLE 1.—REQUIRED ACTIONS

For model * * * As listed in * * * Dated * * * Do these actions * * * No later than * * *

727–100 and 727–200 series.Boeing Service Bulletin

727–25–0294.

May 25, 2000 .................... Modify the escape slide

latch assembly.

36 months after the effective date of this AD.

737–100, –200, –300,

–400, and –500 series.

Boeing Service Bulletin

737–25–1405.

......do ................................ ......do ................................ Do.

737–600, –700, and –800

series.

Boeing Special Attention

Service Bulletin 737–25–

1403.

May 4, 2000 ...................... Install a cover assembly

on the trigger housing of

the inflation cylinder on

the escape slides.

18 months after the effective date of this AD.

737–600, –700, and –800

series.

Boeing Service Bulletin

737–25–1404.

May 25, 2000 .................... Modify the escape slide

latch assembly.

Do.

757–200 and –200CB series.Boeing Service Bulletin

757–25–0217.

......do ................................ ......do ................................ 36 months after the effective date of this AD.

757–300 series .................. Boeing Service Bulletin

757–25–0218.

......do ................................ ......do ................................ Do.

Spares

(b) After the effective date of this AD, no person may install an escape slide assembly or escape slide latch assembly listed

in the ‘‘Existing Part Number’’ column of the table under paragraph 2.E. in the following service bulletins, on any airplane:

TABLE 2.—SPARE PARTS

For Models * * * Listed in * * * Service bulletin date

727–100 and 727–200 series ......................... Boeing Service Bulletin 727–25–0294 .............................................. May 25, 2000

737–100, –200, –300, –400, and –500 series Boeing Service Bulletin 737–25–1405 .............................................. Do.

737–600, –700, and –800 series .................... Boeing Special Attention Service Bulletin 737–25–1403 ................. May 4, 2000.

737–600, –700, and –800 series .................... Boeing Service Bulletin 737–25–1404 .............................................. May 25, 2000.

757–200 and –200CB series .......................... Boeing Service Bulletin 757–25–0217 .............................................. Do.

757–300 series ............................................... Boeing Service Bulletin 757–25–0218 .............................................. Do.

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, 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

(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.

Issued in Renton, Washington, on February

9, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3856 Filed 2–14–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–330–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes Powered

By Pratt & Whitney JT9D–3 and –7

Series Engines

AGENCY: Federal Aviation

Administration, DOT.

10388 Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Boeing Model 747 series airplanes, that

currently requires repetitive inspections

and torque checks of the hanger fittings

and strut forward bulkhead of the

forward engine mount and adjacent

support structure, and corrective

actions, if necessary. The existing AD

also provides for optional terminating

action for the repetitive inspections and

checks. This action would mandate

certain new repetitive torque checks and

the previously optional terminating

action. The actions specified by the

proposed AD are intended to prevent

loose fasteners and associated damage to

the hanger fittings and bulkhead of the

forward engine mount, which could

result in separation of the engine from

the airplane.

DATES: Comments must be received by

April 2, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

330–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmnprmcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–330–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

the proposed rule may be obtained from

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Tamara Anderson, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2771; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this action may be changed in light

of the comments received.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–330–AD.’’

The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

2000–NM–330–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On November 8, 2000, the FAA issued

AD 2000–23–16, amendment 39–11988

(65 FR 69862, November 21, 2000),

applicable to certain Boeing Model 747

series airplanes, to require repetitive

inspections and torque checks of the

hanger fittings and strut forward

bulkhead of the forward engine mount

and adjacent support structure, and

corrective actions, if necessary. (On

December 21, 2000, a correction to that

AD was published in the Federal

Register (65 FR 80301).) That action also

provides for optional terminating action

for the repetitive inspections and

checks. That action was prompted by

reports indicating the detection of loose

fasteners of the hanger fittings and strut

forward bulkhead of the forward engine

mount. The requirements of that AD are

intended to detect and correct loose

fasteners and associated damage to the

hanger fittings and bulkhead of the

forward engine mount, which could

result in separation of the engine from

the airplane.

Actions Since Issuance of Previous Rule

In the preamble to AD 2000–23–16,

the FAA indicated that the actions

required by that AD were considered

‘‘interim action’’ and that it was

considering a separate rulemaking

action to mandate accomplishment of

the terminating action described in Part

6 of Boeing Alert Service Bulletin 747–

54A2203, dated August 31, 2000, which

would terminate the repetitive

inspections and checks required by that

AD. The FAA also indicated that it was

considering mandating the torque

checks described in Part 3 of the alert

service bulletin. The FAA now has

determined that further rulemaking

action is indeed necessary, and this

proposed AD follows from that

determination.

Explanation of Relevant Service

Information

The FAA previously reviewed and

approved Boeing Alert Service Bulletin

747–54A2203, dated August 31, 2000,

which describes procedures for

repetitive detailed visual inspections

and torque checks of the hanger fittings

and strut forward bulkhead of the

forward engine mount and adjacent

support structure to detect loose

fasteners, cracking, and/or damage; and

corrective actions, if necessary. The

corrective actions consist of a torque

check, before further flight, if any loose

fasteners are detected; rework of loose

hanger fittings and damaged or cracked

fittings that are within the allowable

rework limits; and replacement if

damage or cracks are detected that are

outside the allowable rework limits.

If certain damage of the strut forward

bulkhead, bulkhead chords, lower spar

web, or bulkhead channel is detected,

the alert service bulletin specifies

contacting Boeing for rework/

replacement instructions. The alert

service bulletin also describes

procedures for a terminating action,

which eliminates the need for the

repetitive inspections and checks. The

Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules 10389

terminating action involves rework or

replacement of the fittings.

Explanation of Requirements of

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

supersede AD 2000–23–16 to continue

to require repetitive inspections and

torque checks of the hanger fittings and

strut forward bulkhead of the forward

engine mount and adjacent support

structure, and corrective actions, if

necessary. This proposed AD would

mandate certain new repetitive torque

checks and the previously optional

terminating action. The actions would

be required to be accomplished in

accordance with the alert service

bulletin described previously, except as

discussed below.

Differences Between Alert Service

Bulletin and This Proposed AD

Operators should note that, although

the effectivity section of the alert service

bulletin includes Boeing Model 747

series airplanes having serial numbers

21048 and 20887, these airplanes have

been modified and are now powered by

General Electric CF6–50 series engines,

and are not affected by the actions

required by this proposed rule.

Operators also should note that,

although the alert service bulletin

specifies that the manufacturer may be

contacted for certain rework and/or

replacement instructions, this AD

requires such rework and/or

replacement to be done in accordance

with a method approved by the FAA, or

in accordance with data meeting the

type certification basis of the airplane

approved by a Boeing Company

Designated Engineering Representative

who has been authorized by the FAA to

make such findings.

Cost Impact

There are approximately 366

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

115 airplanes of U.S. registry would be

affected by this proposed AD.

The detailed visual inspections that

are currently required by AD 2000–23–

16 take approximately 8 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

inspections currently required by the

existing AD on U.S. operators is

estimated to be $55,200, or $480 per

airplane, per inspection.

The torque checks that are currently

required by AD 2000–23–16 take

approximately 24 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

torque checks currently required by the

existing AD on U.S. operators is

estimated to be $165,600, or $1,440 per

airplane, per check.

The new torque checks proposed in

this AD action also would take

approximately 8 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of this

torque check on U.S. operators is

estimated to be $55,200, or $480 per

airplane, per check.

The terminating action proposed in

this AD action would take

approximately 24 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $300 per airplane. Based

on these figures, the cost impact of the

terminating action proposed by this AD

on U.S. operators is estimated to be

$200,100, or $1,740 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or proposed 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 proposed herein

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. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that this 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) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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 amendment 39–11988 (65 FR

80301, December 21, 2000), and by

adding a new airworthiness directive

(AD), to read as follows:

Boeing: Docket 2000–NM–330–AD.

Supersedes AD 2000–23–16,

Amendment 39–11988.

Applicability: Model 747 series airplanes,

certificated in any category, as listed in

Boeing Alert Service Bulletin 747–54A2203,

dated August 31, 2000; except Model 747

series airplanes having serial numbers 21048

and 20887.

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 loose fasteners and associated

damage to the hanger fittings and strut

forward bulkhead of the forward engine

mount, which could result in separation of

the engine from the airplane, accomplish the

following:

Restatement of Requirements of AD 2000–

23–16

Repetitive Inspections/Checks

(a) Within 60 days after December 6, 2000

(the effective date of AD 2000–23–16,

amendment 39–11988): Perform a detailed

visual inspection and torque check as

10390 Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules

specified in Part 2 of the Accomplishment

Instructions of Boeing Alert Service Bulletin

747–54A2203, dated August 31, 2000, to

detect loose fasteners and associated damage

to the hanger fittings and bulkhead of the

forward engine mount, in accordance with

Figure 1 of the alert service bulletin.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(1) If no loose fastener or associated

damage is detected, repeat the inspections/

checks thereafter at the applicable intervals

specified in Figure 1 of the alert service

bulletin until accomplishment of the

terminating action specified in paragraph (c)

of this AD.

Note 3: Where there are differences

between the AD and the alert service

bulletin, the AD prevails.

Corrective Actions

(2) If any loose fastener or associated

damage is detected, before further flight,

perform the applicable corrective actions

(torque check, rework or replacement of

fittings), as specified in Figure 1 of the alert

service bulletin. Repeat the inspections/

checks thereafter at the applicable intervals

specified in Figure 1 of the alert service

bulletin until accomplishment of the

terminating action specified in paragraph (c)

of this AD. Where the alert service bulletin

specifies that the manufacturer may be

contacted for disposition of certain corrective

actions (rework or replacement of fittings),

this AD requires such rework and/or

replacement to be done in accordance with

a method approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA; or

in accordance with data meeting the type

certification basis of the airplane approved

by a Boeing Company designated engineering

representative (DER) who has been

authorized by the Manager, Seattle ACO, to

make such findings. For a repair method to

be approved by the Manager, Seattle ACO, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

New Requirements of This AD

Repetitive Checks/Inspections/Corrective

Actions

(b) Within 18 months after the effective

date of this AD: Do the torque check

specified in Part 3 of the Accomplishment

Instructions of Boeing Alert Service Bulletin

747–54A2203, dated August 31, 2000, to

detect loose fasteners of the hanger fittings of

the forward engine mount.

(1) If no loose fastener is detected, repeat

the torque check thereafter at intervals not to

exceed 1,200 flight cycles or 18 months,

whichever occurs first, until accomplishment

of the terminating action specified in

paragraph (c) of this AD.

(2) If any loose fastener is detected, before

further flight, perform the applicable

corrective actions as specified in Figure 4,

Figure 5, or Part 6, as applicable, of the

Accomplishment Instructions of the alert

service bulletin.

(i) If Figure 4 or Figure 5 of the

Accomplishment Instructions of the alert

service bulletin is used to do the corrective

actions for the fitting; thereafter, repeat the

detailed visual inspection required by

paragraph (a) of this AD at the applicable

intervals specified in Figure 1 of the alert

service bulletin, and repeat the torque check

for that fitting at intervals not to exceed 180

flight cycles. Accomplish the terminating

action for that fitting as specified in Part 6

of the Accomplishment Instructions of the

alert service bulletin within 18 months after

finding any loose fastener or 60 months after

the effective date of this AD, whichever

occurs first.

(ii) If Part 6 of the Accomplishment

Instructions of the alert service bulletin is

used to do the corrective actions for the

fitting, this constitutes terminating action for

the repetitive inspections/checks for that

fitting only.

(3) If any associated damage is found,

before further flight, repair in accordance

with a method approved by the Manager,

Seattle Aircraft Certification Office (ACO),

FAA; or in accordance with data meeting the

type certification basis of the airplane

approved by a Boeing Company designated

engineering representative (DER) who has

been authorized by the Manager, Seattle

ACO, to make such findings. For a repair

method to be approved by the Manager,

Seattle ACO, as required by this paragraph,

the Manager’s approval letter must

specifically reference this AD. If any damage

to any fitting is found, before further flight,

do the applicable corrective actions specified

in Part 4 or Part 5 of the Accomplishment

Instructions of the alert service bulletin; this

constitutes terminating action for the

repetitive inspections/checks for that fitting

only.

(4) If any loose fastener is detected during

any repeat inspection/check specified in

paragraph (b)(2)(i) of this AD, before further

flight, accomplish the terminating action for

that fitting as specified in Part 6 of the

Accomplishment Instructions of the alert

service bulletin.

Terminating Action

(c) Within 60 months after the effective

date of this AD: Accomplish all actions in the

terminating action specified in Part 6 of the

Accomplishment Instructions of Boeing Alert

Service Bulletin 747–54A2203, dated August

31, 2000. Accomplishment of this paragraph

constitutes terminating action for the

repetitive inspections/checks required by

paragraphs (a) and (b) of this AD. Where the

alert service bulletin specifies that the

manufacturer may be contacted for

disposition of certain corrective actions

(rework or replacement of fittings), this AD

requires such rework and/or replacement to

be done in accordance with a method

approved by the Manager, Seattle ACO; or in

accordance with data meeting the type

certification basis of the airplane approved

by a Boeing Company DER who has been

authorized by the Manager, Seattle ACO, to

make such findings. For a repair method to

be approved by the Manager, Seattle ACO, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

Note 4: Installation of two

BACW10BP*APU washers on Group A

fasteners accomplished during modification

in accordance with Boeing Service Bulletin

747–54A2159, dated November 3, 1994,

Revision 1, dated June 1, 1995, or Revision

2, dated March 14, 1996; and pin or bolt

protrusion as specified in the 747 Structural

Repair Manual, Chapter 51–30–02 (both

referenced in Boeing Alert Service Bulletin

747–54A2203, dated August 31, 2000); is

considered acceptable for compliance with

the terminating action specified in 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, Seattle

ACO. 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 5: 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

(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.

Issued in Renton, Washington, on February

9, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3857 Filed 2–14–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–327–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–100 and –200 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness