4904 Federal Register / Vol. 62, No. 22 / Monday, February 3, 1997 / Rules and Regulations

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 prevent front compressor front hub (fan

hub) failure due to tierod, counterweight, or

bushed hole cracking, which could result in

an uncontained engine failure and damage to

the aircraft, accomplish the following:

(a) For fan hubs identified by serial

numbers (S/Ns) in Appendix A of PW Alert

Service Bulletin (ASB) No. A6272, dated

September 24, 1996, after the fan hub has

accumulated more than 4,000 cycles in

service since new (CSN), accomplish the

following:

(1) Select an initial inspection interval

from Table 1 of this AD and inspect for

cracks in accordance with the

Accomplishment Instructions, Paragraph A,

Part 1, and, if applicable, Paragraph B, of PW

ASB No. A6272, dated September 24, 1996.

(2) Reinspect at the interval in Table 1 of

this AD that corresponds to the selected

initial inspection interval, and in accordance

with the Accomplishment Instructions,

Paragraph A, Part 1, and, if applicable,

Paragraph B, of PW ASB No. A6272, dated

September 24, 1996.

TABLE 1

Initial inspection Reinspection

1. Within 1,050 cycles

in service (CIS)

after the effective

date of this AD, or

prior to accumulating 5,050 CSN,

whichever occurs

later.

After accumulating

2,500 CIS since

last inspection, but

not to exceed

6,000 CIS since

last inspection.

OR

2. Within 990 CIS

after the effective

date of this AD, or

prior to accumulating 4,990 CSN,

whichever occurs

later.

After accumulating

2,500 CIS since

last inspection, but

not to exceed

8,000 CIS since

last inspection.

TABLE 1—Continued

Initial inspection Reinspection

OR

3. Within 965 CIS

after the effective

date of this AD, or

prior to accumulating 4,965 CSN,

whichever occurs

later.

After accumulating

2,500 CIS since

last inspection, but

not to exceed

10,000 CIS since

last inspection.

(b) For fan hubs with S/Ns not listed in

Appendix A of PW ASB No. A6272, dated

September 24, 1996, after the fan hub has

accumulated more than 4,000 CSN, inspect at

the next time the fan hub is in the shop at

piece-part level, but not to exceed 10,000 CIS

after effective date of this AD in accordance

with the Accomplishment Instructions,

Paragraph A, Part 2, and, if applicable,

Paragraph B, of PW ASB No. A6272, dated

September 24, 1996.

(c) Remove from service fan hubs found

cracked or fan hubs that exceed the bushed

hole acceptance criteria in accordance with

PW ASB No. A6272, dated September 24,

1996, and replace with serviceable parts.

(d) Report findings of cracked fan hubs in

accordance with Accomplishment

Instructions, Paragraph F, of Attachment 1 to

PW ASB No. A6272, dated September 24,

1996, within 48 hours after inspection to

Robert Guyotte, Manager, Engine

Certification Branch, Engine Certification

Office, FAA, Engine and Propeller

Directorate, 12 New England Executive Park,

Burlington, MA 01803–5299; telephone (617)

238–7142, fax (617) 238–7199; Internet:

Robert.Guyotte@faa.dot.gov. Reporting

requirements have been approved by the

Office of Management and Budget and

assigned OMB control number 2120–0056.

(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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(g) The actions required by this AD shall

be done in accordance with the following PW

ASB:

Document

No. Pages Revision Date

A6272 ........ 1–21 OriginalSeptember

24, 1996.

NDIP–892 .. 1–30 A September

15, 1996.

Document

No. Pages Revision Date

Attachment

I.

AI–1–

AI–4 A September

15, 1996.

Total pages: 55.

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 Pratt & Whitney, 400 Main St., East

Hartford, CT 06108; telephone (860) 565–

6600, fax (860) 565–4503. Copies may be

inspected at the FAA, New England Region,

Office of the Assistant Chief Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street NW., Suite 700,

Washington, DC.

(h) This amendment becomes effective on

March 5, 1997.

Issued in Burlington, Massachusetts, on

January 13, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–1703 Filed 1–31–97; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–106–AD; Amendment

39–9910; AD 97–03–04]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 727 and 737 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 727

and 737 series airplanes, that requires

replacing the fuel cap assembly with a

new assembly on the inlet fitting at the

inside top of the Boeing-designed

auxiliary fuel tank(s). This amendment

also requires installing certain new

placards once the replacement action is

accomplished. This amendment is

prompted by reports that the fuel cap

assembly, due to its design, became

loose and allowed fuel to enter the

deactivated auxiliary fuel tanks on inservice airplanes. The actions specified

by this AD are intended to prevent

unwanted fuel transferring to the

deactivated auxiliary fuel tanks, due to

the problems associated with a loose

fuel cap assembly.

DATES: Effective March 10, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director
Federal Register / Vol. 62, No. 22 / Monday, February 3, 1997 / Rules and Regulations 4905

of the Federal Register as of March 10,

1997.

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,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington; telephone (206) 227–2686;

fax (206) 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 727 and 737 series airplanes was

published in the Federal Register on

June 19, 1996 (61 FR 31061). That action

proposed to require replacing the fuel

cap assembly with a new assembly on

the inlet fitting at the inside top of the

auxiliary fuel tank. That action also

proposed to require the replacement of

currently-installed ‘‘INOP’’ placards

with new placards.

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 Rule

One commenter supports the

proposal.

Request To Clarify Applicability of the

Proposed Rule

One commenter requests clarification

as to what airplanes would be subject to

the proposed AD. The commenter

points out that, although the

applicability statement of the proposal

indicates that it is applicable to all

Boeing Model 737 series airplanes, the

referenced Boeing Alert Service Bulletin

737–28A1032 applies only to Model

737–200 series airplanes. The

commenter questions whether the

proposed rule would be applicable to all

other types of Model 737’s that are

equipped with forward an/or aft

auxiliary fuel tanks.

The FAA concurs that clarification is

needed with respect to the applicability

of this AD. First, this AD addresses

problems associated only with certain

Boeing-designed auxiliary fuel tanks.

Those fuel tanks are installed only on

airplanes specified in the effectivity

listing of Boeing Alert Service Bulletin

727–28A0062, Revision 5, dated May 4,

1995 (for Model 727 series airplanes),

and Boeing Alert Service Bulletin 737–

28A1032, Revision 2, dated May 4, 1995

(for Model 737–200 series airplanes).

The final rule has been revised to

specify that:

1. the airplanes subject to the AD are

the ones specified in those Boeing alert

service bulletins, and

2. the subject auxiliary fuel tanks are

designed by Boeing.

Request for Clarification Regarding

Future Applicability of Proposed Rule

One commenter requests clarification

as to whether airplanes whose auxiliary

fuel tanks are not currently deactivated,

would be subject to the requirements of

the proposed rule if their auxiliary fuel

tanks were to be deactivated at some

time in the future.

The FAA concurs that clarification is

necessary regarding this point. The

applicability statement clearly specifies

that the AD is applicable to airplanes

with deactivated auxiliary fuel tanks.

Therefore, the AD is applicable to any

airplane whenever its auxiliary fuel tank

is deactivated—now or at any time in

the future. The FAA has added a NOTE

to the final rule to specify that the

requirements of the AD become

applicable whenever an auxiliary fuel

tank is deactivated on the subject

airplanes.

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 211 Boeing

Model 727 series airplanes and 36

Boeing Model 737 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 134 Boeing

Model 727 series airplanes and 25

Boeing Model 737 series airplanes of

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

For Boeing Model 727 series

airplanes, the required modification will

take approximately 53 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts will be supplied by the

manufacturer at no cost to the operators.

Based on these figures, the cost impact

of the AD on U.S. operators of Model

727 series airplanes is estimated to be

$426,120, or $3,180 per airplane.

For Boeing Model 737 series

airplanes, the required modification will

take approximately 18 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts will be supplied by the

manufacturer at no cost to the operators.

Based on these figures, the cost impact

of the AD on U.S. operators of Model

737 series airplanes is estimated to be

$27,000, or $1,080 per airplane.

The cost impact figure discussed

above is 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 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.

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:
4906 Federal Register / Vol. 62, No. 22 / Monday, February 3, 1997 / Rules and Regulations

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:

97–03–04—Boeing: Amendment 39–9910.

Docket 95–NM–106–AD.

Applicability: Model 727 and 737

airplanes; as listed in Boeing Alert Service

Bulletin 727–28A0062, Revision 5, dated

May 4, 1995 (for Model 727 series airplanes)

and Boeing Alert Service Bulletin 737–

28A1032, Revision 2, dated May 4, 1995 (for

Model 737 series airplanes); equipped with

forward and/or aft Boeing-designed auxiliary

fuel tanks that have been deactivated;

certificated in any category.

Note 1: If the forward and/or aft Boeingdesigned auxiliary fuel tank(s) on any of the

airplanes specified in the applicability

provision is currently activated, the

requirements of this AD become applicable

whenever that auxiliary fuel tank is

deactivated.

Note 2: 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 (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 the nut of the fuel cap assembly

from backing off and the cap from loosening,

and subsequently, unwanted fuel transferring

to the auxiliary fuel tanks, accomplish the

following:

(a) Within 6 months after the effective date

of this AD, accomplish paragraphs (a)(1) and

(a)(2) of this AD, in accordance with Part IV

of the Accomplishment Instructions of

Boeing Alert Service Bulletin 727–28A0062,

Revision 5, dated May 4, 1995 (for Model 727

series airplanes); or Boeing Alert Service

Bulletin 737–28A1032, Revision 2, dated

May 4, 1995 (for Model 737 series airplanes);

as applicable.

(1) Replace the fuel cap assembly having

part number (P/N) AN929A24 with a new

fuel cap assembly having P/N AN929L24 on

the inlet fitting at the inside top of the

auxiliary fuel tank, in accordance with the

applicable service bulletin. And

(2) Replace the INOP placards with new

placards, in accordance with the applicable

service bulletin.

(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,

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, Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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.

(d) The actions shall be done in accordance

with Boeing Alert Service Bulletin 727–

28A0062, Revision 5, dated May 4, 1995 (for

Model 727 series airplanes); or Boeing Alert

Service Bulletin 737–28A1032, Revision 2,

dated May 4, 1995 (for Model 737 series

airplanes); 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.

(e) This amendment becomes effective on

March 10, 1997.

Issued in Renton, Washington, on January

23, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–2223 Filed 1–31–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–235–AD; Amendment

39–9911; AD 97–03–05]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain McDonnell

Douglas DC–9 series airplanes, that

currently requires repetitive visual

inspections to detect corrosion and

cracking of the fuselage upper skin and

frames in the area of the loop antenna

assemblies of the automatic direction

finder (ADF), and repair, if necessary.

This amendment adds a requirement to

perform a visual and an eddy current

inspection of the fuselage forward upper

skin under the antennas, followed by

the reinstallation of the ADF antennas

using an improved procedure. This

amendment is prompted by the

development of a modification of the

ADF antenna installation that

constitutes terminating action for the

required repetitive visual inspections.

The actions specified by this AD are

intended to prevent rapid

decompression of the fuselage,

significant structural damage, and

subsequent reduced structural integrity

of the airplane, due to problems

associated with corrosion and fatigue

cracking in the subject area.

DATES: Effective March 10, 1997.

The incorporation by reference of

McDonnell Douglas Alert Service

Bulletin DC9–53A282, dated March 20,

1996, listed in the regulations, was

approved previously by the Director of

the Federal Register, in accordance with

5 U.S.C. 552(a) and 1 CFR part 51, as of

April 15, 1996 (61 FR 15882, April 10,

1996).

The incorporation by reference of

McDonnell Douglas Service Bulletin

DC9–53–284, dated August 20, 1996,

listed in the regulations, is approved by

the Director of the Federal Register as of

March 10, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from McDonnell Douglas Corporation,

3855 Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Department C1–L51 (2–60). 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 FAA,

Transport Airplane Directorate, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Wahib Mina, Aerospace Engineer,

Airframe Branch, ANM–120L, FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712; telephone (310) 627–

5324; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 96–07–51,

amendment 39–9562 (61 FR 15882,

April 10, 1996), which is applicable to

certain McDonnell Douglas DC–9 series

airplanes, was published in the Federal

Register on October 23, 1996 (61 FR

54969). That action proposed to

continue to require repetitive internal