Federal Register / Vol. 62, No. 239 / Friday, December 12, 1997 / Rules and Regulations 65355

Certification Office (ACO), FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, WA 98055–4056; fax (425) 227–

1181. The report shall include the

information specified in paragraphs (f)(1),

(f)(2), (f)(3), (f)(4), and (f)(5) of this AD.

Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget (OMB) under the provisions of the

Paperwork Reduction Act of 1980 (44 U.S.C.

3501 et seq.) and have been assigned OMB

Control Number 2120–0056.

(1) The airplane serial number.

(2) The total hours time-in-service

accumulated on the airplane.

(3) The total number of flight cycles

accumulated on the airplane.

(4) A description of any damage found.

(5) The location of where the damaged part

was installed.

(g) For airplanes having line numbers 433

and subsequent: Within 14 days after

accomplishing the initial inspection required

by paragraph (a) of this AD, submit any

damaged part to the Manager, Seattle ACO.

The damaged part shall be tagged to include

the information specified in paragraphs (f)(1),

(f)(2), (f)(3), (f)(4), and (f)(5) of this AD.

Additionally, operators shall align the inner

sleeving, outer sleeving, and wire as installed

in the airplane, and secure the sleeving and

wiring in place by taping or other means

when submitting the damaged part to the

Manager, Seattle ACO. Information collection

requirements contained in this regulation

have been approved by the OMB under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

(h) 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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.

(j) The actions shall be done in accordance

with Boeing Alert Service Bulletin 747–

28A2204, dated December 19, 1996, or

Boeing Service Bulletin 747–28A2204,

Revision 1, dated October 30, 1997.

(1) The incorporation by reference of

Boeing Service Bulletin 747–28A2204,

Revision 1, dated October 30, 1997, 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 Alert Service Bulletin 747–28A2204,

dated December 19, 1996, was approved

previously by the Director of the Federal

Register as of January 21, 1997 (62 FR 304,

January 3, 1997).

(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.

(k) This amendment becomes effective on

December 29, 1997.

Issued in Renton, Washington, on

December 9, 1997.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–32611 Filed 12–11–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–282–AD; Amendment

39–10239; AD 97–25–15]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 727 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Boeing Model 727

series airplanes. This action requires

repetitive inspections to detect cracking

of the rear spar web or fuel leakage of

the wing center section, and repair, if

necessary. This amendment also

provides for an optional modification of

the rear spar web that constitutes

terminating action for the repetitive

inspections. This amendment is

prompted by several reports of fuel

leakage due to cracking of the rear spar

web of the wing center section. The

actions specified in this AD are

intended to detect and correct such

cracking of the rear spar web, which

could permit fuel leakage into the

airflow multiplier, and could result in

an electrical short that could cause a

fire.

DATES: Effective December 29, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

29, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

February 10, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

282–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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 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.

FOR FURTHER INFORMATION CONTACT:

Walter Sippel, Aerospace Engineer,

Airframe Branch, ANM–120S, Seattle

Aircraft Certification Office, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2774;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received reports indicating that fuel

leakage of the wing center section has

occurred on several Boeing Model 727

series airplanes due to cracking of the

rear spar web of the wing center section.

The cracking initiates on the forward

side of the spar and propagates through

the web at the upper machined land

radius between Left Body Buttock Line

(BBL) 40 and Right BBL 40. In two

instances, cracking was reported on

airplanes that had accumulated less

than 25,000 total flight cycles. In

another case, fuel leakage resulted in

fuel odors being emitted into the cabin

area. Investigation revealed that fuel

was leaking into the airflow multiplier.

Fuel leakage into the airflow multiplier

due to cracking of the rear spar web of

the wing center section, if not detected

and corrected, could result in an

electrical short that could cause a fire.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 727–

57A0182, dated September 18, 1997.

This alert service bulletin describes

procedures for removing the access

panels of the wing center section to

perform repetitive visual inspections

using a borescope, or ultrasonic with

high frequency eddy current

inspections, to detect cracking of the

rear spar web or fuel leakage of the wing

center section, and repair, if necessary.

In addition, the alert service bulletin

describes procedures for modification of

the rear spar web of the wing center

section to prevent cracking of the rear

spar web, which eliminates the need for

the repetitive inspections the

modification involves stop drilling any
65356 Federal Register / Vol. 62, No. 239 / Friday, December 12, 1997 / Rules and Regulations

cracking, and repairing the rear spar

web.

The alert service bulletin references

Boeing Drawing 65C37620 as an

additional source of service information

for accomplishment of the repair and

modification.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other Boeing Model 727

series airplanes of the same type design,

this AD is being issued to detect and

correct cracking of the rear spar web,

which could permit fuel leakage into the

airflow multiplier and resultant

electrical shorting and fire. This AD

requires repetitive inspections [either

visual inspections using a borescope or

a mirror, or ultrasonic and high

frequency eddy current (HFEC)

inspections] to detect cracking of the

rear spar web or fuel leakage of the wing

center section, and repair, if necessary.

This AD also provides for an optional

modification of the rear spar web of the

wing center section, which constitutes

terminating action for the repetitive

inspection requirements of this AD. The

inspections, certain repairs, and the

modification are required to be

accomplished in accordance with the

alert service bulletin described

previously. Certain repairs are required

to be accomplished in accordance with

a method approved by the FAA.

Operators should note the following

differences between this AD and the

Boeing alert service bulletin:

• Although the alert service bulletin

recommends an initial inspection

threshold of within 500 flight cycles for

airplanes that have accumulated

between 15,000 and 25,000 total flight

cycles, and an initial inspection

threshold of within 300 flight cycles for

airplanes that have accumulated 25,000

or more total flight cycles, this AD

specifies an initial compliance time of

‘‘prior to the accumulation of 15,000

total flight cycles, or within 300 flight

cycles after the effective date of this AD,

whichever occurs later.’’ The FAA finds

that, in view of the reports of cracking

of the rear spar web on two airplanes

that had accumulated less than 25,000

total flight cycles, the initial compliance

time specified in this AD is appropriate.

Further, the FAA finds that adequate

justification for permitting an inspection

threshold of 500 flight cycles for

airplanes that have accumulated over

15,000 total flight cycles, but under

25,000 total flight cycles, has not been

presented. Therefore, an initial

inspection is required to be

accomplished on all airplanes within

300 flight cycles after the effective date

of this AD.

• This AD requires that, for any

cracking or fuel leakage detected that is

outside the areas specified in the alert

service bulletin, repair must be

accomplished in accordance with a

method approved by the FAA.

• This AD requires that the access

panel only be opened in order to

perform the inspections, rather than

removed, as described in the Boeing

alert service bulletin. The manufacturer

has advised the FAA that procedures to

remove the access panels were

inadvertently included in the alert

service bulletin and will be removed at

the next revision of the alert service

bulletin.

• Although the alert service bulletin

describes procedures for performing the

visual inspection using a borescope, the

manufacturer has advised the FAA that

the option of performing the visual

inspection using a mirror was

inadvertently omitted from the alert

service bulletin. Moreover, Figure 1 of

the Accomplishment Instructions of the

alert service bulletin specifies that the

subject area can be examined with a

borescope or mirror. Therefore, the FAA

has included the option of using a

mirror as an acceptable method of

compliance with the visual inspection

requirements of this AD.

Interim Action

This is considered to be interim

action. The FAA is currently

considering requiring the modification

of the rear spar web of the wing center

section, which will constitute

terminating action for the repetitive

inspections required by this AD.

However, the planned compliance time

for the installation of the modification is

sufficiently long so that notice and

opportunity for prior public comment

will be practicable.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–282–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, may be obtained from the
Federal Register / Vol. 62, No. 239 / Friday, December 12, 1997 / Rules and Regulations 65357

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:

97–25–15 Boeing: Amendment 39–10239.

Docket 97–NM–282–AD.

Applicability: Model 727 series airplanes

having line numbers 858 through 864

inclusive, 867 through 869 inclusive, 872

through 883 inclusive, and 885 through 1832

inclusive; certificated in any category.

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 (e) 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 detect and correct cracking of the rear

spar web, which could permit fuel leakage

into the airflow multiplier, and could result

in an electrical short that could cause a fire,

accomplish the following:

(a) Prior to the accumulation of 15,000 total

flight cycles, or within 300 flight cycles after

the effective date of this AD, whichever

occurs later: Accomplish the inspections

specified in either paragraph (a)(1) or (a)(2)

of this AD, in accordance with Boeing Alert

Service Bulletin 727–57A0182, dated

September 18, 1997. For purposes of this AD,

the access panels specified in the alert

service bulletin need not be removed; the

access panels need only be opened.

Note 2: The fuel tank of the wing center

section may be filled with fuel to assist in

detecting cracking or fuel leakage during the

accomplishment of the visual inspections

required by this AD.

(1) Perform a visual inspection using a

borescope or mirror to detect cracking of the

rear spar web and/or fuel leakage of the wing

center section between Right Body Buttock

Line (BBL) 40 and Left BBL 40, in accordance

with Part I of the Accomplishment

Instructions of the alert service bulletin.

Thereafter, repeat this inspection at intervals

not to exceed 300 flight cycles. Or

(2) Perform an ultrasonic and high

frequency eddy current (HFEC) inspection to

detect cracking of the rear spar web of the

wing center section between Right BBL 40

and Left BBL 40, in accordance with Part II

of the Accomplishment Instructions of the

alert service bulletin. Thereafter, repeat this

inspection at intervals not to exceed 3,000

flight cycles.

(b) If any cracking of the rear spar web and/

or fuel leakage of the wing center section is

detected between Right BBL 40 and Left BBL

40 near the upper machined land radius,

prior to further flight, repair in accordance

with Part III of the Accomplishment

Instructions in Boeing Alert Service Bulletin

727–57A0182, dated September 18, 1997.

Accomplishment of this repair constitutes

terminating action for the repetitive

inspection requirements of this AD.

(c) If any cracking of the rear spar web and/

or fuel leakage of the wing center section is

detected that is outside the area specified in

paragraph (b) of this AD, prior to further

flight, repair in accordance with a method

approved by the Manager, Seattle Aircraft

Certification Office (ACO), FAA, Transport

Airplane Directorate.

(d) Accomplishment of paragraphs (d)(1)

and either (d)(2) or (d)(3) of this AD, as

applicable, constitute terminating action for

the repetitive inspection requirements of this

AD.

(1) Accomplish an ultrasonic and HFEC

inspection in accordance with the

requirements of paragraph (a)(2) of this AD.

And,

(2) If no cracking is detected, prior to

further flight, modify the rear spar web of the

center section of the fuel tank between Right

BBL 40 and Left BBL 40, in accordance with

the Accomplishment Instructions of Boeing

Alert Service Bulletin 727–57A0182, dated

September 18, 1997.

(3) If any cracking is detected, prior to

further flight, repair in accordance with the

Accomplishment Instructions of Boeing Alert

Service Bulletin 727–57A0182, dated

September 18, 1997.

(e) 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Manager, Seattle ACO.

(f) 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, provided the

limitations specified in paragraphs (f)(1)

through (f)(6) of this AD are included in the

special flight permit:

‘‘(1) Required trip and reserve fuel must be

carried in the No. 1 and No. 3 outer wing

tanks.

(2) Wing center tank No. 2 must be empty

of fuel.

(3) The fuel system must be checked for

normal operation prior to flight by verifying

that all boost pumps are operational;

configuring the fuel system by turning on all

boost pumps in the No. 1 and 3 outer wing

tanks and by opening all crossfeed valve

selectors; and by confirming that fuel is not

bypassing tank No. 2 check valves by

observing that there is no leakage into tank

No. 2.

(4) Maintain a minimum of 5,300 pounds

of fuel in tanks No. 1 and No. 3 to prevent

uncovering the fuel bypass valve.

(5) The fuel quantity indication system

must be operational in all three tanks.

(6) The effects of loading fuel only in the

wing tanks on the airplane weight and

balance must be considered and accounted

for.’’

(g) Except as provided by paragraph (c) of

this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 727–57A0182, dated September 18,

1997. 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.

(h) This amendment becomes effective on

December 29, 1997.

Issued in Renton, Washington, on

December 3, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–32233 Filed 12–11–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 95–ASO–21]

RIN 2120–AA66

Modification of Jet Route J–46

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This rule extends Jet Route J–

46 from Volunteer, TN, to Alma, GA.