Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Rules and Regulations 63831

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 copy of the final

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.

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 a new airworthiness directive

(AD) to read as follows:

97–25–02 Mitsubishi Heavy Industries:

Amendment 39–10225; Docket No. 97–

CE–22–AD.

Applicability: Models MU–2B, MU–2B–10,

MU–2B–15, MU–2B–20, MU–2B–25, MU–

2B–26, MU–2B–30, MU–2B–35, MU–2B–36,

MU–2B–36A, MU–2B–40, and MU–2B–60

airplanes, all serial numbers, 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 (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 within the next 30

days after the effective date of this AD, unless

already accomplished.

To prevent loss of airplane control or

engine overspeed with consequent loss of

engine power caused by the power levers

being positioned below the flight idle stop

while the airplane is in flight, accomplish the

following:

(a) Amend the Limitations Section of the

airplane flight manual (AFM) by inserting the

following language:

Positioning of power levers below the

flight idle stop while the airplane is in flight

is prohibited. Such positioning may lead to

loss of airplane control or may result in an

overspeed condition and consequent loss of

engine power.

(b) This action may be accomplished by

incorporating a copy of this AD into the

Limitations Section of the AFM.

(c) Amending the AFM, as required by this

AD, may be performed by the owner/operator

holding at least a private pilot certificate as

authorized by section 43.7 of the Federal

Aviation Regulations (14 CFR 43.7), and must

be entered into the aircraft records showing

compliance with this AD in accordance with

section 43.9 of the Federal Aviation

Regulations (14 CFR 43.9).

(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.

(e) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (ACO), FAA, 1801

Airport Road, Wichita, Kansas. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(f) Information related to this AD may be

examined at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

(g) This amendment (39–10225) becomes

effective on January 21, 1998.

Issued in Kansas City, Missouri, on

November 25, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–31675 Filed 12–2–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–33–AD; Amendment 39–

10224; AD 97–25–01]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company 58, 60, 90, 100, 200,

and 300 Series and Model 2000

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all Raytheon Aircraft

Company (Raytheon) 58, 60, 90, 100,

200, and 300 series and Model 2000

airplanes (formerly referred to as Beech

58, 60, 90, 100, 200, and 300 series and

Beech Model 2000 airplanes). This AD

requires replacing certain AlliedSignal

Aerospace outflow/safety valves in the

pressurization system with new or

serviceable valves. The AD results from

a report of cracking and consequent

failure of the affected outflow safety

valves in the pressurization system.

Investigation has revealed problems

during the manufacturing process of

certain AlliedSignal outflow/safety

valves. The actions specified by this AD

are intended to prevent outflow/safety

valve cracking and consequent failure,

which could result in rapid

decompression of the airplane.

EFFECTIVE DATE: January 11, 1998.

ADDRESSES: Service information that

applies to the proposed AD may be

obtained from AlliedSignal Aerospace,

Technical Publications, Department 65–

70, P.O. Box 52170, Phoenix, Arizona

85072–2170. This information also may

be examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–33–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT:

Michael D. Imbler, Aerospace Engineer,

FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas

67209; telephone (316) 946–4147;

facsimile (316) 946–4407.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would
63832 Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Rules and Regulations

apply to all Raytheon 58, 60, 90, 100,

200, and 300 series and Model 2000

airplanes was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on August 4, 1997

(62 FR 41901). The NPRM proposed to

require replacing any of the following

AlliedSignal outflow/safety valves with

new or serviceable valves:

Valve model Valve serial numbers Airplane models installed in

103570–26 ............. 80–223, 80–225 through 80–227, 80–229, and 80–230 .................................................. 2000.

103598–2 ............... 16–808, 39–2434, 45–747, 87–1600, and 116–1238 ....................................................... 60(A), C90, and E90.

103598–15 ............. 128–11 ............................................................................................................................... 58P.

103648–1 ............... 11–4913 through 11–4916, 12–3832, 20–3006, 22–4950, 12–3912, 30–3076, 39–

2412, 41–4918, 41–4919, 61–3300, 101–4920, 101–4922 through 101–4924, 101–

4926 through 101–4931, 101–4933, 101–4935, 101–4936, 101–4938, 101–4940,

101–4941, 121–3683, 121–4942, 129–2904, and 129–2920.

60, 90, A90, B90, C90, E90, 100,

A100, and B100.

103648–3 ............... 21–1827, 71–1828, 71–1829, and 120–1823 through 101–1826 .................................... 58P.

103648–4 ............... 10–4664 through 10–4667, 11–223, 11–3093, 11–3161, 11–4717 through 11–4721,

12–795, 12–3641, 12–4760, 15–4368, 21–3182, 21–3208, 21–4722 through 21–

4728, 21–4730, 21–4732, 22–3688, 22–3706, 22–3733, 22–3736, 24–4232, 24–

4241, 24–4252, 24–4255, 27–4498, 32–3756, 32–3777, 32–4761, 32–4762, 37–

1087, 37–1113, 38–2417, 41–3227, 41–3237, 41–3261, 41–3274, 41–4733, 41–

4734, 42–1475, 42–3830, 42–3838, 42–3840, 42–3850, 42–3851, 42–3877, 42–

3882, 42–3883, 42–3890, 48–1557, 49–181, 50–2804, 51–4735, 51–4736, 59–2090,

60–2896, 61–3301, 61–4737, 61–4738, 62–3907, 62–3968, 62–3981, 62–2155, 70–

2960, 71–4739, 71–4740, 72–3988, 72–3991, 72–3999, 74–4288, 74–4289, 74–

4293, 74–4296, 76–4441, 77–4556, 77–4567, 79–2189, 79–2218, 79–2223, 81–

3415, 87–1197, 87–1585, 89–2288, 95–4404, 99–2358, 99–2365, 99–2369, 99–

2385, 99–2403, 99–2430, 104–4336, 107–1297, 110–3033, 111–3462, 111–3482,

111–3515, 111–4755, 116–4468, 116–4470, 119–2507, 119–2520, 120–3043, 120–

3048, 120–3057, 120–4687 through 120–4692, 121–3562, 126–4490, 128–1776,

and 129–4639.

200.

103648–5 ............... 10–325, 12–760, 12–799, 20–236, 21–1734, 21–1741 through 21–1744, 21–1746, 40–

365, 21–1762, 41–1763, 60–243, 61–605, 77–1590, 90–461, 100–1712 through

100–1718, 100–1720 through 100–1726, 100–1728 through 100–1731, 105–149,

105–285, 109–1613, 109–1620, 116–1488, 121–1764, 126–1502, and 126–1511.

C90–1, C90A, and F90.

103648–6 ............... 101–1830, 101–1831, and 110–1822. .............................................................................. 58P and 90.

103648–7 ............... 11–208, 14–1206, 17–2204, 21–2817, 21–2818, 21–2827, 21–2828, 22–2832, 23–

1030, 23–1058, 24–1211, 24–1232, 25–1634, 30–2719, 31–346, 42–843, 51–397,

51–398, 51–409, 54–1253, 74–1320, 77–2349, 86–2136, 103–1129, 110–1171,

112–961, 112–1000, 113–1172, 113–1192, 114–1538, 118–2569, 119–2607, 119–

2614, 101–2796 through 100–2806, and 100–2808 through 100–2815.

B200 and 300.

103648–13 ............. 12–410, 12–464, 12–465, and 70–386 through 70–400 .................................................. 300 and B300.

The NPRM resulted from a report of

cracking and consequent failure of the

affected outflow safety valves in the

pressurization system. Investigation has

revealed problems during the

manufacturing process of certain

AlliedSignal outflow/safety valves.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the one

comment received on the proposal. No

comments have been received regarding

the FAA’s estimate of the cost impact

upon the public.

Comment Disposition

Raytheon states that the FAA made

the following typographical errors in the

Applicability section of the NPRM:

—Model B300 airplane serial numbers

were referenced as F1–1 through F1–72

instead of FL–1 through FL–72; and

—Model 200T airplane serial numbers

were referenced as B–1 through BT–32

instead of BT–1 through BT–32.

Raytheon requests that the FAA include

the correct serial number designations

for these airplanes in the final rule.

The FAA concurs with the

commenter. The FAA inadvertently

referenced the wrong serial numbers for

the Models 200T and B300 airplanes.

The final rule will reflect the correct

serial number designations for these

airplanes.

Similar Actions Required on the

Affected Airplanes

On August 12, 1996, the FAA issued

AD 96–17–10, Amendment 39–9719 (61

FR 42996, August 20, 1996), which

requires replacing the outflow/safety

valves with serviceable valves on

certain Raytheon Model 400, 400A,

MU–300–10, and 2000 airplanes, and

200, B200, 300, and B300 series

airplanes. The FAA inadvertently

included the Raytheon 200, B200, 300,

and B300 series and Model 2000

airplanes in the applicability of AD 96–

17–10. These airplanes are certificated

under part 23 of the Federal Aviation

Regulations (14 CFR part 23), and the

FAA has determined that these

airplanes should be addressed in this

AD along with certain other Raytheon

airplanes certificated under 14 CFR part

23. The Raytheon Models 400, 400A,

and MU–300–10 airplanes are

certificated under part 25 of the Federal

Aviation Regulations (14 CFR part 25).

The FAA is revising AD 96–17–10 in

another action to retain the

requirements for the airplanes

certificated under 14 CFR part 25.

Compliance Time of This AD

The FAA has determined that an

interval of 4 months is an appropriate

compliance time to address the

identified unsafe condition in a timely

manner. This compliance time was

deemed appropriate after considering

the safety implications, the average

utilization rate of the affected fleet, and

the availability of the replacement parts.

In addition, this compliance time will

coincide with the compliance time

originally included in AD 96–17–10 of

18 months after the effective date

(effective date: September 24, 1996 plus

18 months = March 24, 1998). The 4-

month compliance time of this AD will

coincide with the compliance time

included in AD 96–17–10. Both actions

will be required around March 1998.
Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Rules and Regulations 63833

Cost Impact

The FAA estimates that 2,386

airplanes in the U.S. registry will be

affected by this AD, that it will take

approximately 12 workhours per

airplane to accomplish the required

action, and that the average labor rate is

approximately $60 an hour.

AlliedSignal will provide parts at no

cost to the owner/operator. Based on

these figures, the total cost impact of

this AD on US operators is estimated to

be $1,717,920, or $720 per airplane. The

FAA knows of no affected airplane

owner/operator that has already

accomplished the required action.

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 copy of the final

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.

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 a new airworthiness directive

(AD) to read as follows:

97–25–01 Raytheon Aircraft Company:

Amendment 39–10224; Docket No. 97–

CE–33–AD.

Applicability: 58, 60, 90, 100, 200, and 300

series and Model 2000 airplanes (all serial

numbers), certificated in any category. The

following charts present airplane models and

serial numbers that are equipped with

AlliedSignal Aerospace outflow safety valves

as referenced in either AlliedSignal

Aerospace Service Bulletin 103570–21–4012,

Revision 1, dated May 30, 1995; Service

Bulletin 103648–21–4022, Revision 1, dated

May 30, 1995; or Service Bulletin 103598–

21–4024, Revision 1, dated May 30, 1995.

—The airplanes presented in the charts are

affected by paragraph (a) of this AD.

—All airplanes are affected by paragraph

(b) of this AD.

AIRPLANE MODELS AND SERIAL NUMBERS THAT ARE EQUIPPED WITH ALLIEDSIGNAL OUTFLOW VALVES

Models Serial numbers

58P and 58PA ........................................................ TJ–3 through TJ–497.

60 and A60 ............................................................. P–3 through P–246 with Kit No. 60–5024–1 S incorporated.

B60 ......................................................................... P–247 through P–307 with Kit No. 60–5024–3 S incorporated.

B60 ......................................................................... P–308 through P–596.

65–90, A90, B90, C90, and C90A ......................... LJ–1 through LJ–1302.

E90 ......................................................................... LW–1 through LW–347.

F90 .......................................................................... LA–2 through LA–236.

100 and A100 ......................................................... B–1 through B–94, B–100 through B–204, and B–206 through B–247.

B100 ....................................................................... BE–1 through BE–137.

200 and B200 ......................................................... BB–2, and BB–6 through BB–1419.

200C and B200C .................................................... BL–1 through BL–23, BL–25 through BL–57, and BL–61 through BL–137.

200T ........................................................................ BT–1 through BT–32.

200CT and B200CT ............................................... BN–1 through BN–4.

300 .......................................................................... FA–1 through FA–220, and FF–1 through FF–19.

B300 ....................................................................... FL–1 through FL–72.

B300C ..................................................................... FM–1, FM–2, and FM–3.

2000 ........................................................................ NC–4 through NC–53.

H90 (T44A) ............................................................. LL–1 through LL–61.

A100 (U–21F) ......................................................... B–95 through B–99.

A100–1 (U21J) ....................................................... BB–3, BB–4, and BB–5.

A200 (C12–A/C) ..................................................... BD–1 through BD–30, and BC–1 through BC–75.

A200 (UC–12B) ...................................................... BJ–1 through BJ–66.

A200CT (C–12D) .................................................... BP–1, BP–22, and BP–24 through BP–51.

A200CT (FWC–12D) .............................................. BP–7 through BP–11.

A200CT (RC–12D) ................................................. GR–1 through GR–13.

A200CT (C–12F) .................................................... BP–52 through BP–63.

A200CT (RC–12G) ................................................. FC–1, FC–2, and FC–3.

A200CT (RC–12H) ................................................. GR–14 through GR–19.

A200CT (RC–12K) ................................................. FE–1 through FE–9.

B200C (C–12F) ...................................................... BL–73 through BL–112, and BL-118 through BL–123.

B200C (UC–12F) .................................................... BU–1 through BU–10.

B200C (RC–12F) .................................................... BU–11 and BU–12.

B200C (UC–12M) ................................................... BV–1 through BV–10.

B200C (RC–12M) ................................................... BV–11 and BV–12.

B200C (C–12F) ...................................................... BP–64 through BP–71.

B200CT (FWC–12D) .............................................. FG–1 and FG–2.
63834 Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Rules and Regulations

APPLICABLE OUTFLOW SAFETY VALVES WITH APPLICABLE AIRPLANE MODELS

Valve model Valve serial numbers Airplane models installed in

103570–26 ............. 80–223, 80–225 through 80–227, 80–229, and 80–230 .................................................. 2000.

103598–2 ............... 16–808, 39–2434, 45–747, 87–1600, and 116–1238 ....................................................... 60(A), C90, and E90.

103598–15 ............. 128–11 ............................................................................................................................... 58P.

103648–1 ............... 11–4913 through 11–4916, 12–3832, 20–3006, 22–4950, 12–3912, 30–3076, 39–

2412, 41–4918, 41–4919, 61–3300, 101–4920, 101–4922 through 101–4924, 101–

4926 through 101–4931, 101–4933, 101–4935, 101–4936, 101–4938, 101–4940,

101–4941, 121–3683, 121–4942, 129–2904, and 129–2920.

60, 90, A90, B90, C90, E90, 100,

A100, and B100.

103648–3 ............... 21–1827, 71–1828, 71–1829, and 120–1823 through 101–1826 .................................... 58P.

103648–4 ............... 10–4664 through 10–4667, 11–223, 11–3093, 11–3161, 11–4717 through 11–4721,

12–795, 12–3641, 12–4760, 15–4368, 21–3182, 21–3208, 21–4722 through 21–

4728, 21–4730, 21–4732, 22–3688, 22–3706, 22–3733, 22–3736, 24–4232, 24–

4241, 24–4252, 24–4255, 27–4498, 32–3756, 32–3777, 32–4761, 32–4762, 37–

1087, 37–1113, 38–2417, 41–3227, 41–3237, 41–3261, 41–3274, 41–4733, 41–

4734, 42–1475, 42–3830, 42–3838, 42–3840, 42–3850, 42–3851, 42–3877, 42–

3882, 42–3883, 42–3890, 48–1557, 49–181, 50–2804, 51–4735, 51–4736, 59–2090,

60–2896, 61–3301, 61–4737, 61–4738, 62–3907, 62–3968, 62–3981, 62–2155, 70–

2960, 71–4739, 71–4740, 72–3988, 72–3991, 72–3999, 74–4288, 74–4289, 74–

4293, 74–4296, 76–4441, 77–4556, 77–4567, 79–2189, 79–2218, 79–2223, 81–

3415, 87–1197, 87–1585, 89–2288, 95–4404, 99–2358, 99–2365, 99–2369, 99–

2385, 99–2403, 99–2430, 104–4336, 107–1297, 110–3033, 111–3462, 111–3482,

111–3515, 111–4755, 116–4468, 116–4470, 119–2507, 119–2520, 120–3043, 120–

3048, 120–3057, 120–4687 through 120–4692, 121–3562, 126–4490, 128–1776,

and 129–4639.

200.

103648–5 ............... 10–325, 12–760, 12–799, 20–236, 21–1734, 21–1741 through 21–1744, 21–1746, 40–

365, 21–1762, 41–1763, 60–243, 61–605, 77–1590, 90–461, 100–1712 through

100–1718, 100–1720 through 100–1726, 100–1728 through 100–1731, 105–149,

105–285, 109–1613, 109–1620, 116–1488, 121–1764, 126–1502, and 126–1511.

C90–1, C90A, and F90.

103648–6 ............... 101–1830, 101–1831, and 110–1822 ............................................................................... 58P and 90.

103648–7 ............... 11–208, 14–1206, 17–2204, 21–2817, 21–2818, 21–2827, 21–2828, 22–2832, 23–

1030, 23–1058, 24–1211, 24–1232, 25–1634, 30–2719, 31–346, 42–843, 51–397,

51–398, 51–409, 54–1253, 74–1320, 77–2349, 86–2136, 103–1129, 110–1171,

112–961, 112–1000, 113–1172, 113–1192, 114–1538, 118–2569, 119–2607, 119–

2614, 101–2796 through 100–2806, and 100–2808 through 100–2815.

B200 and 300.

103648–13 ............. 12–410, 12–464, 12–465, and 70–386 through 70–400 .................................................. 300 and B300.

Note 1: The above outflow/safety valves are

referenced in AlliedSignal Aerospace Service

Bulletin 103570–21–4012, Revision 1, dated

May 30, 1995; Service Bulletin 103648–21–

4022, Revision 1, dated May 30, 1995; and

Service Bulletin 103598–21–4024, Revision

1, dated May 30, 1995. In addition,

Beechcraft Service Bulletin 2484, Revision 1,

dated October, 1995, references the

AlliedSignal service bulletins.

Note 2: 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 in the

body of this AD, unless already

accomplished.

To prevent outflow/safety valve cracking

and consequent failure, which could result in

rapid decompression of the airplane,

accomplish the following:

(a) For the airplanes referenced in the

‘‘Airplane Models and Serial Numbers That

Are Equipped with AlliedSignal Outflow

Valves’’ table that is included in the

‘‘Applicability’’ section of this AD: Within

the next 4 months after the effective date of

this AD, replace (with a new or serviceable

valve) any outflow/safety valve that does not

have one of the following:

(1) The valve identification plate MOD

RECORD stamped ‘‘PCA’’ (Poppet Change

Accomplished); or

(2) A valve with an inked ATD Quality

Assurance ‘‘Functional Test (FT)’’ stamp that

is dated June 1992, or later.

(b) For all airplanes: As of the effective

date of this AD, no person may install on any

affected airplane any outflow/safety valve

that is referenced in the ‘‘Applicable Outflow

Safety Valves With Applicable Airplane

Models’’ table that is included in the

‘‘Applicability’’ section of this AD.

(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) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas 67209. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(e) All persons affected by this directive

may obtain copies of the documents referred

to herein upon request to AlliedSignal

Aerospace, Technical Publications,

Department 65–70, P.O. Box 52170, Phoenix,

Arizona 85072–2170; or may examine these

documents at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

(f) This amendment (39–10224) becomes

effective on January 11, 1998.

Issued in Kansas City, Missouri, on

November 25, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–31676 Filed 12–2–97; 8:45 am]

BILLING CODE 4910–13–U